Spacecraft and Experiments

NSSDC/ WDC-A-R&S

Supplement No. 1 to the January 1974 Report on Active and Planned Spacecraft and Experiments

(NASA-TM-X-6991 3) SUPPLEMENT NO. 1 TO N74-3027 THE JANUARY 1974 REPORT ON ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS (NASA) CSCL 22A Unclas p5- G3/30 45603 JULY 1974

Reproduced by NATIONAL TECHNICAL INFORMATION SERVICE US Department of Commerce Springfield, VA. 22151 NSSDC/WDC-A-R&S

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION * GODDARD SPACE FLIGHT CENTER, GREENBELT, MD. NSSDC/WDC-A-R&S 74-12

SUPPLEMENT NO. 1 TO THE

JANUARY 1974 REPORT ON ACTIVE AND PLANNED

SPACECRAFT AND EXPERIMENTS

Edited by

Richard Horowitz and Leo R. Davis National Space Science Data Center

July 1974

National Space Science Data Center (NSSDC)/ World Data Center A for Rockets and Satellites (WDC-A-R&S) National Aeronautics and Space Administration Goddard Space Flight Center Greenbelt, Maryland 20771 Page intentionally left blank PREFACE

This supplement to the Report on Active and Planned Spacecraft and Experiments provides the professional community with information on current as well as planned spacecraft activity in a broad range of scientific disciplines. The document provides brief descriptions for spacecraft and experiments that were not listed in the original report or the content of which has significantly changed from that previously reported due to information recently received. Current data regarding expected launch dates and operation and performance data are presented for all spacecraft and experiments that were active or planned as of March 31, 1974.

We would like to acknowledge the cooperation of the acquisition scientists and others at the National Space Science Data Center (NSSDC) in obtaining information and offering suggestions for this supplement. We are most appreciative of the efforts of the on-site contractor at NSSDC, Programming Methods, Inc. (PMI) Facilities Management Corpora- tion, in preparing this document for publication. Also, the cooperation of the project offices and experimenters in supplying current documentation of their spacecraft and experiments is gratefully acknowledged. We are particularly pleased with the many constructive comments and corrections we have received from interested readers.

NSSDC plans to publish a new cumulative report within 6 months; subsequent plans call for quarterly supplements and an annual cumulative report.

July 1974 Richard Horowitz Leo R. Davis

iii TABLE OF CONTENTS

Page

PREFACE ...... '...... vii INTRODUCTION :......

SECTION 1 - SUPPLEMENTARY DESCRIPTIONS OF ACTIVE AND 1001 PLANNED SPACECRAFT AND EXPERIMENTS ...... 1083 SECTION 2 - INDEXES ......

2.1 - Cumulative Index of Active and Planned 1085 Spacecraft and Experiments ...... 2.2 - Cumulative Bar Graph Indexes for Electromagnetic Radiation Experiments ...... 1117

SECTION 3 - SPACECRAFT AND EXPERIMENTS LAUNCHED OR INACTIVATED BETWEEN APRIL 1, 1973, AND 1123 MARCH 31, 1974 ...... 1125 3.1 - Spacecraft Launched ...... 3.2 - Spacecraft and Experiments Which Became Operational Off ...... 1133 3.3 - Spacecraft and.Experiments Which Became 1137 Inoperable ...... 1141 SECTION 4 - RECENT NSSDC DATA ACQUISITIONS ......

NOT FILMED pE PAG BLANK

V INTRODUCTION

The purpose of this supplement to the Report on Active and Planned Spacecraft and Experiments is to provide updated information and descriptions on the spacecraft and experiments described therein. This includes spacecraft and experiments that have become known to NSSDC since the original report was published or the descriptions of which have changed significantly from that previously reported. In general, the contents, availability, definitions, abbreviations, and acronyms described in the Introduction to the annual report are applicable to this supplement and will not be repeated here.

Several changes have been made to the organization of the report in an effort to simplify its use. Sections 1 and 2 of the original report have been combined to form Section 1 of the supplement. The spacecraft and experiment descriptions in Section 1 of the supplement are now sorted by the spacecraft common name and the principal investigator's last name (instead of by NSSDC ID code). Thus, a particular description can now usually be located without reference to the index. -In addition to these changes, the Explorer spacecraft prelaunch generic names will be used as common names (i.e., IMP-H instead of Explorer 47). This, coupled with the new sort order, places prelaunched and launched spacecraft for a given project series in a contiguous sequence. Hope- fully, this change will simplify locating descriptions of spacecraft by listing names that are familiar to the user. The location of -spacecraft descriptions within the report may still be identified by alternate names using the index in Section 2.1. This cumulative index not only serves as an index to the location of spacecraft and experiment descriptions but also includes other useful information, such as the operational status and data rate, in a convenient and useful format. A set of bar graphs covering electromagnetic radiation is included in Section 2.2.

Several of the changes just noted were suggested by interested readers. We again wish to solicit such suggestions and comments as well as notifications of errors or omissions.

PRECEDING AG

vii SECTION 1 - SUPPLEMENTARY DESCRIPTIONS OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS

This section contains descriptions of spacecraft and experiments, both active and planned, that have become known to NSSDC since the original report was published or the descriptions of which have changed significantly from that previously reported.

The descriptions are sorted first by spacecraft common name. Within each spacecraft listing, experiments are ordered by the principal investigator's last name. If the common name, as used by NSSDC, is not known, it can be found by referring to an alternate name found in the index in Section 2.1.

For more detailed information on the contents of the descriptions, the reader is referred to page 1 of the January 1974 report.

1i81 NATIONAL SPACE SCIENCE DATA CENTER ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS

##******9#*****t#*********+#*$4**#****#*******APOLLO 16 LM/ALSEP ***********

SPACECRAFT COMMON NAME- APOLLO 16 LM/ALSEP ALTERNATE NAMES- ALSEP 16, LEM 16, ROVER 16, 06005. APOLLO 16C NSSDC ID- 72-031C

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 04/21/72.

LAUNCH DATE- 04/16/72 SPACECRAFT WEIGHT IN ORBIT- 5040. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- SATURN 5

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OMSF UNITED STATES NASA-OSS

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER* PS=PROJECT SCIENTIST)

SPACECRAFT BRIEF DESCRIPTION THE APOLLO 16 LUNAR MODULE (LM) CONSISTED OF A LUNAR LANDING CRAFT, A LUNAR ROVING VEHICLE (LRV), AND AN APOLLO LUNAR SURFACE EXPERIMENT PACKAGE (ALSEP) THAT CONTAINED SCIENTIFIC EXPERIMENTS TO BE LEFT ON THE LUNAR SURFACE AFTER COMPLETION OF THE MANNED PORTION OF THE MISSION. THE LM LANDED IN THE DESCARTES HIGHLAND REGION JUST NORTH OF THE CRATER DOLLAND AT 8 DEG 59 MIN 55 SEC S LATITUDE, AND 15 DEG 31 MIN 12 SEC E LONGITUDE. THE ALSEP WAS DEPLOYED AT THE LANDING SITE. THE LRV WAS USED DURING EXTRA VEHICULAR ACTIVITIES (EVA) TO EXTEND THE RANGE OF MANNED LUNAR EXPLORATION. THE NUCLEAR POWERED ALSEP PACKAGE CONTAINED SEISMIC, MAGNETIC FIELD, HEAT FLOW* LUNAR SOIL COMPOSITION, SOLAR WIND, AND COSMIC-RAY EXPERIMENTS.

************APOLLO 16 LM/ALSEP, DYAL

EXPERIMENT NAME- LUNAR SURFACE MAGNETOMETER NSSDC ID- 72-031C-03

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 08/17/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - P. DYAL NASA-ARC MOFFETT FIELD, CA OI - C.W. PARKIN NASA-ARC MOFFETT FIELD* CA OI - C.P. SONETT U OF ARIZONA TUCSON, AZ

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT CONSISTED OF A TRIAXIAL FLUXGATE MAGNETOMETER INTENDED TO MEASURE THE LOCAL MAGNETIC FIELD AT THE SURFACE OF THE MOON. IT WAS INTENDED TO YIELD INFORMATION ON THE MOON'S INTERNAL ELECTRICAL CHARACTERISTICS. staggest########## ##############** **** *********CORSA *************

SPACECRAFT COMMON NAME- CORSA ALTERNATE NAMES- COSMIC RAY SATELLITE NSSDC ID- CORSA PRECEDING PAGE BLANK NOT FILMED

1003 LAST REPORTED STATE- A PROPOSED MISSION

PLANNED LAUNCH DATE- 1975 SPACECRAFT WEIGHT IN ORBIT- 70. KG

LAUNCH SITE- KAGOSHIMA, JAPAN LAUNCH VEHICLE- M-3S-C

SPONSORING COUNTRY/AGENCY JAPAN TOKYO U

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 600. KM ALT PERIAPSIS- 350. KM ALT INCLINATION- 30. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - M. ODA U OF TOKYO TOKYO, JAPAN PS - S. HAYAKAWA NAGOYA U NAGOYA* JAPAN

SPACECRAFT BRIEF DESCRIPTION THE OBJECTIVES OF THE COSMIC RADIATION SATELLITE, CORSA. ARE TO MAKE MEASUREMENTS OF COSMIC X RAYS AND HEAVY PRIMARY PARTICLES. THESE ARE REDUCED GOALS RELATIVE TO THE ORIGINAL PRCGRAM, WHICH WAS THE MEASUREMENT CF COSMIC X RAYS, GAMMA RAYS, ALPHA PARTICLES, AND HEAVY NUCLEI. AN ENGINEERING MODEL OF THE SATELLITE INCORPORATING ALL FOUR EXPERIMENT PACKAGES WAS CONSTRUCTED AND EVALUATED IN 1971-72. ON THE BASIS OF THE STUDY OF THE ENGINEERING MODEL, A DECISION WAS MADE IN 1973 TO CANCEL THE GAMMA-RAY AND ALPHA PARTICLE EXPERIMENT PACKAGES. THE X-RAY DETECTORS ARE TO BE POSITIONED SO THAT THEY MAY VIEW THE SKY IN TWO ORTHOGONAL DIRECTIONS, I.E., PARALLEL AND PERPENDICULAR TO THE SPIN AXIS OF THE SATELLITE. THE OBSERVATIONS WILL COVER THE ENERGY INTERVAL FROM 0.25 KEV TO 60 KEV. THE COSMIC RAY HEAVY PARTICLE TELESCOPE WILL DETERMINE THE NUCLEAR CHARGE OF THE PRIMARIES AND FOR EACH SPECIES GIVE DATA ON THE INTEGRAL ENERGY SPECTRUM OVER THE RANGE FROM 3 TO 6 GEV. CORSA WILL HAVE A CYLINDRICAL SHAPE WITH A DIAMETER OF 85 CM AND A HEIGHT OF APPROXIMATELY 90 CM. THE SPACECRAFT WILL BE SPIN STABILIZED, WITH THE ORIENTATION OF THE AXIS CONTROLLABLE BY COMMAND. A TOTAL ELECTRIC POWER OF APPROXIMATELY 15 WATTS WILL BE PROVIDED BY 6000 SOLAR CELLS MOUNTED ON THE SIDE SURFACE OF THE SATELLITE. A SUN SENSOR AND HORIZON SENSOR WILL BE UTILIZED AS ASPECT-METER. AN ONBOARD CORE MEMORY OF 4000 EIGHT-BIT WORDS IS TO BE USED TO STORE THE DATA DURING THE TIME WHEN THE SATELLITE IS OUT OF RANGE OF GROUND TELEMETRY STATIONS. THE PROPOSED ORBIT IS NEARLY CIRCULAR AT AN ALTITUDE OF ABOUT 500 KM AND WITH AN INCLINATION OF 30 DEGREES.

************CORSA, HAYAKAWA

EXPERIMENT NAME- COSMIC X-RAY DETECTION (0.25 - 60 KEV) NSSDC ID- CORSA -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - S. HAYAKAWA NAGOYA U NAGOYA, JAPAN

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL BE FOR THE DETECTION OF COSMIC X RAYS. THERE WILL BE TWO SETS OF TWO UNITS OF GAS-FILLED PROPORTIONAL COUNTERS THAT CAN MEASURE VERY-SOFT AND SOFT X RAYS. THESE TWO SETS WILL BE POSITIONED WITHIN THE SATELLITE TO VIEW THE SKY IN TWO ORTHOGONAL DIRECTIONS, PARALLEL AND PERPENDICULAR TO THE SPIN AXIS WHICH WILL BE CONTROLLABLE BY COMMAND. THEREFORE MEASUREMENTS WILL BE ABLE TO BE MADE OF ANY INTERESTING X-RAY

1004 OBJECT ON THE CELESTIAL SPHERE. IN ADDITION, THERE WILL BE ONE RAYS. SCINTILLATION COUNTER ON THE SATELLITE FOR THE DETECTION OF HARD X OVER THE FULL X-RAY INSTRUMENTATION PACKAGE WILL BE ABLE TO DETECT X RAYS UP TO 1.3 THE INTERVAL FROM 0.25 KEV TO 60 KEV, AND WITH A TIME RESOLUTION MSEC.

************CORSA, ODA

EXPERIMENT NAME- COSMIC HEAVY PRIMARY PARTICLES NSSDC ID- CORSA -02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - M. ODA U OF TOKYO TOKYO, JAPAN

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT IS TO MEASURE CCSMIC-RAY HEAVY PRIMARY PARTICLES USING WILL BE A SOLIO-STATE PARTICLE TELESCOPE. THE NUCLEAR CHARGE OF PARTICLE RESOLVED IN THE ENERGY RANGE FROM 3 TO 6 GEV.

ELMS 1 ************** +*#******### t*****t*B+***** * 44***** ******

SPACECRAFT COMMON NAME- ELMS 1 ALTERNATE NAMES- BMS, SESP P73-4. ST 73-4A, P 73-4 NSSDC ID- ELMS 1

LAST REPORTED STATE-_ AN APPROVED MISSION

1091. KG PLANNED LAUNCH DATE- 07/00/75 SPACECRAFT WEIGHT IN ORBIT-

VEHICLE- ATLAS-BUR2 LAUNCH SITE- VANDENBERG AFB, UNITED STATES LAUNCH

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-USAF

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN INCLINATION- 67. DEG APOAPSIS- 630. KM ALT PERIAPSIS- 630. KM ALT

SCIENTIST) SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT LOS ANGELES, CA PS - J.V. KENNEDY USAFSAMSO

SPACECRAFT BRIEF DESCRIPTION THIS SPACECRAFT WILL BE AN INDEPENDENT SELF-SUSTAINING UNIT, THE 960-CU FT. CONSISTING OF ONE EXPERIMENT AND ITS SUPPORTING SYSTEMS. POWER SPACECRAFT WILL OBSERVE EARTH LIMB RADIANCES AND WILL HAVE SUFFICIENT ONLY ABOUT TO OPERATE CONTINUOUSLY OVER ITS PLANNED 20-DAY LIFETIME. SINCE TO THE ONE-TENTH OF THE SPACECRAFT WEIGHT AND VOLUME WILL BE ATTRIBUTED WILL BE SENSOR. IT APPEARS THAT MUCH OF THE SPACECRAFT WEIGHT AND VOLUME OCCUPIED BY THE POWER SUPPLY, SENSOR COCLING SYSTEM, 3-AXIS STABILIZATION SYSTEM, AND TELEMETRY.

2 *************** ***t**#******** ***#*****8**+****** * *ELMS

SPACECRAFT COMMON NAME- ELMS 2 P 74-3 ALTERNATE NAMES- BMS SESP P74-3, ST 74-3A, NSSOC ID- ELMS 2

1005 LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 10/00/75 SPACECRAFT WEIGHT IN CRBIT- 1091. KG

LAUNCH SITE- VANDENBERG AFB, UNITED STATES LAUNCH VEHICLE- ATLAS-BUR2

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-USAF

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 630. KM ALT PERIAPSIS- 630. KM ALT INCLINATION- 67. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PS - J.V. KENNEDY USAFSAMSO LOS ANGELES, CA

SPACECRAFT BRIEF DESCRIPTION THIS SPACECRAFT WILL BE AN INDEPENDENT SELF-SUSTAINING UNIT, CONSISTING OF ONE EXPERIMENT AND ITS SUPPORTING SYSTEMS. THE 960-CU-FT SPACECRAFT WILL OBSERVE EARTH LIMB RADIANCES AND WILL HAVE SUFFICIENT POWER TO OPERATE CONTINUOUSLY OVER ITS PLANNED 20-DAY LIFETIME. IT APPEARS THAT MUCH OF THE SPACECRAFT WEIGHT AND VOLUME WILL BE OCCUPIED BY THE POWER SUPPLY, SENSOR COOLING SYSTEM, 3-AXIS STABILIZATION SYSTEM, AND TELEMETRY, SINCE ONLY ABOUT ONE-TENTH OF THE SPACECRAFT WEIGHT AND VOLUME IS ATTRIBUTED TO THE SENSOR.

*** ****4** ***************~**+**************GEOS-C

SPACECRAFT COMMON NAME- GEOS-C ALTERNATE NAMES- GEODETIC SATELLITE-C NSSDC ID- GEOS-C

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- UNSCHED. SPACECRAFT WEIGHT IN CRBIT- 241.0 KG

LAUNCH SITE- VANDENBERG AFO, UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OA

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 103.5 MIN APOAPSIS- 964. KM ALT PERIAPSIS- 890. KM ALT INCLINATION- 115. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER* PS=PROJECT SCIENTIST) PM - D.S. DILLER NASA HEADQUARTERS WASHINGTON. DC PS - J.P. MURPHY NASA HEADQUARTERS WASHINGTON, DC

SPACECRAFT BRIEF DESCRIPTION THE SPACECRAFT WILL CONSIST OF AN OCTAHEDRON, TOPPED BY A TRUNCATED PYRAMID. WITH A PARABOLIC REFLECTOR FOR A RADAR ALTIMETER ON THE FLAT BOTTOM SIDE. A METAL RIBBON BOOM WITH END MASS WILL EXTEND UPWARD APPROXIMATELY 20 FT FROM THE TOP OF THE PYRAMID. PASSIVE LASER RETROREFLECTOR CUBES WILL BE MOUNTED IN A RING AROUND THE PARABOLIC REFLECTOR WITH THE NORMAL VECTOR FROM EACH CUBE FACING 45 DEG OUTWARD FROM THE EARTH DIRECTION OF THE BOOM AXIS. A TURNSTILE ANTENNA FOR VHF AND UHF FREQUENCIES AND SEPARATE ANTENNAS FOR EARTH-VIEWING 324-MHZ DOPPLER, C-BAND, AND S-BAND TRANSPONDERS WILL BE

1006 MOUNTED SEPARATELY ON FLAT SURFACES NEXT TO THE PARABOLIC REFLECTOR. THE DIMENSION ACROSS THE FLATS OF THE OCTAHEDRON WILL BE 48 IN., AND THE SPACECRAFT WILL BE 43.79 IN. HIGH WITH A TOTAL WEIGHT OF 530 LBS. THE MISSION WILL PROVIDE THE STEPPING STONE BETWEEN THE ONGOING NATIONAL GEODETIC SATELLITE PROGRAM (NGSP) AND THE EMERGING EARTH AND OCEAN PHYSICS APPLICATION PROCRAM. IT WILL PROVIDE DATA TO REFINE THE GEODETIC AND GEOPHYSICAL RESULTS OF THE NGSP AND WILL SERVE AS A TEST FOR NEW SYSTEMS. MISSION OBJECTIVES WILL BE TO PERFORM A SATELLITE ALTIMETRY EXPERIMENT IN ORBIT, TO SUPPORT FURTHER THE CALIBRATION AND POSITION DETERMINATION OF NASA AND OTHER AGENCY C-BAND RADAR SYSTEMS, AND TO PERFORM A SATELLITE-TO-SATELLITE TRACKING EXPERIMENT WITH THE ATS-F SPACECRAFT USING AN S-BAND TRANSPONDER SYSTEM. THIS SYSTEM WILL ALSO BE USED FOR PERIODIC GEOS-C TELEMETRY DATA RELAY THROUGH ATS-F, TO SUPPORT FURTHER THE INTERCOMPARISON OF TRACKING SYSTEMS, TO INVESTIGATE THE SOLID-EARTH DYNAMIC PHENOMENA THROUGH PRECISION LASER TRACKING, TO REFINE FURTHER ORBIT DETERMINATION TECHNIQUES AS WELL AS THE DETERMINATION OF INTERDATUM TIES AND GRAVITY MODELS, AND TO SUPPORT THE CALIBRATION AND POSITION DETERMINATION CF NASA-STDN S-BAND TRACKING SYSTEMS.

************GEOS-C, JACKSON

EXPERIMENT NAME- C-BAND SYSTEM NSSDC ID- GEOS-C -03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) Pl - E.B. JACKSON NASA-WS WALLOPS ISLAND. VA

EXPERIMENT BRIEF DESCRIPTION THE C-BAND TRANSPONDER SUBSYSTEM WILL CONSIST OF TWO TRANSPONDERS, ONE THE GEOS-2 NON-COHERENT TYPE AND THE OTHER A COHERENT C-BAND TRANSPONDER. THE NON-COHERENT TRANSPONDER WILL PROVIDE FOR RANGE AND ANGLE MEASUREMENTS, WHILE THE COHERENT TRANSPONDER WILL PROVIDE FOR BOTH RANGE, RANGE-RATE. AND ANGLE MEASUREMENTS. BOTH TRANSPONDERS WILL RECEIVE SIGNALS AT 5690 MHZ, BUT THE COHERENT TRANSPONDER WILL TRANSMIT AT 5690 MHZ. WHILE THE NON-COHERENT TYPE WILL TRANSMIT AT 5765 MHZ. EACH C-BAND TRANSPONDER WILL TRANSMIT ONE PULSE FOR EACH CODED GROUP OF PULSES TRANSMITTED BY A GROUND TRACKING C-BAND RADAR. THE INTERNAL DELAY BET*EEN THE RECEIVED GROUND TRANSMITTED PULSE CODE AND THE TRANSPONDER TRANSMITTED PULSE WILL BE CAREFULLY CALIBRATED PRIOR TO LAUNCh. EACH TRANSPONDER (WHILE OPERATING SEPARATELY OR SIMULTANEOUSLY) WILL BE CAPABLE OF OPERATING IN EITHER OF TWO MODES. STANDBY OR OVERRIDE. IN STANDBY. THE RECEIVER WILL BECOME OPERATIONAL AFTER APPROXIMATELY 60 SEC OF INTERROGATION OR LONG ENOUGH FOR THE OUTPUT TUBE TO WARM UP, WHILE IN THE OVERRIDE MODE OF OPERATION THE OUTPUT TUBE FILAMENT WILL BE ENERGIZED BY THE EXTERNAL COMMAND AND THE WARM-UP DELAY CIRCUIT BYPASSED AFTER THE TUBE WARMS UP, THUS ALLOWING THE TRANSPONDER TO RESPOND IMMEDIATELY TO INTERROGATION SIGNALS. THIS OVERRIDE MODE WILL BE INCORPORATED TO EASE GROUND COMMAND REQUIREMENTS AND TO CONSERVE SPACECRAFT POWER.

************GEOS-C, MINOTT

EXPERIMENT NAME- LASER CUBE SYSTEM NSSDC I0- GEOS-C -04

LAST REPORTED STATE- PRELAUNCH

1007 EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - P. MINOTT NASA-GSFC GREENBELT, MD

EXPERIMENT BRIEF DESCRIPTION LASER CORNER REFLECTORS, COMPOSED OF 270 (MINIMUM) 35-MM CUBES. WILL BE UTILIZED IN CONJUNCTION WITH GROUND-BASED LASER SYSTEMS TO OBTAIN PRECISE SATELLITE TRACKING INFORMATION. THE APPLIED PHYSICS LABORATORY WILL BE RESPONSIBLE FOR PROVIDING THE NECESSARY LASER CUBE REFLECTOR PANELS. THE CUBES WILL BE CONFIGURED ON THE LATERAL SURFACE OF A CONIC FRUSTUM# WITH THE LATERAL SURFACE OF THE FRUSTUM ADJOINING THE BOTTOM, EARTH-ORIENTED SURFACE OF THE SPACECRAFT AT A 45-DEG ANGLE. THE BASE OF THE FRUSTUM WILL MEASURE APPROXIMATELY 0.9 METERS IN DIAM. WHEN ILLUMINATED BY A LASER LIGHT PULSE FROM THE GROUND. EACH RETROREFLECTOR CUBE IN THE ARRAY WILL REFLECT THE LIGHT RAY BACK TO A SPECIAL TELESCOPE RECEIVER ON THE GROUND. THE REFLECTED LIGHT WILL BE PICKED UP BY THE TELESCOPE AND THE OPTICAL IMPULSES CONVERTED TO AN ELECTRICAL SIGNAL. A DIGITAL COUNTER WILL RECORD THE TIME AT WHICH THE BEAM OF LIGHT IS RETURNED TO THE GRCUND. THE TOTAL TRAVEL TIME OF THE LIGHT PULSES, FROM GROUND TO SATELLITE AND BACK TO THE GROUND. WILL MEASURE THE DISTANCE TO THE SATELLITE AND THUS FORM THE BASIS OF THE SATELLITE OPTICAL LASER SYSTEM. THE FOLLOWING OBSERVATIONAL SYSTEMS WILL BE UTILIZEC IN ACQUIRING THE NECESSARY DATA -- NASA/WI LASER RANGING SYSTEMS, SAO LASER RANGING SYSTEMS, GSASER RANGING SYSTEMS, AND OTHER NATIONAL AND INTERNATIONAL LASER STATIONS AS DETERMINED.

*~**********GEOS-Co STANLEY

EXPERIMENT NAME- RACAR ALTIMETER SYSTEM NSSOC ID- GEOS-C -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=GTHER INVESTIGATOR) PI - H.R. STANLEY NASA-WS WALLOPS ISLAND, VA

EXPERIMENT BRIEF DESCRIPTION THE RADAR ALTIMETER EXPERIMENT WILL BE THE HIGHEST PRIORITY EXPERIMENT ABOARD GEOS-C. ITS PURPOSES WILL BE TO DETERMINE THE FEASIBILITY AND UTILITY OF A SPACE-BORNE RADAR ALTIMETER TO MAP THE TOPOGRAPHY OF THE OCEAN SURFACE WITH AN ABSOLUTE ACCURACY WITHIN 5 METERS, AND WITH A RELATIVE ACCURACY OF 1 TC 2 METERS. TO DETERMINE THE FEASIBILITY OF MEASURING THE DEFLECTION OF THE VERTICAL AT SEA. TO DETERMINE THE FEASIBILITY OF MEASURING WAVE HEIGHT, AND TO CONTRIBUTE TO THE TECHNOLOGY LEADING TO A FUTURE OPERATIONAL ALTIMETER-SATELLITE SYSTEM WITH A 10-CM MEASUREMENT CAPABILITY. TO MEET THE OBJECTIVES OF THE EXPERIMENT, THE ALTIMETER WILL HAVE TWO DISTINCT DATA GATHERING MODES - A LONG-PULSE ALTIMETRY DATA MODE AND A SHORT-PULSE MODE. IT IS INTENDED THAT THE PERFORMANCE CAPABILITIES AND OPERATING CHARACTERISTICS OF THE ALTIMETER MAY DIFFER FOR THE TWO MODES. BOTH MODES WILL OPERATE ON A 13.9-GHZ FREQUENCY, BOTH WILL USE A PARABOLIC ANTENNA, BOTH WILL HAVE A MAXIMUM RANGE ACQUISITION TIME OF 6 SEC. AND BOTH WILL HAVE AN ALTITUDE GRANULARITY OF PLUS OR MINUS 0.2 METERS. DIFFERING CHARACTERISTICS WILL BE -- (1) ALTITUDE DATA RATE FOR LONG PULSE WILL BE 2 READING/SEC AND FOR SHORT PULSE 6 READING/SECs AND (2) INPUT POWER FOR LONG PULSE WILL BE 50 W, FOR SHORT PULSE 100 W. THE GEOS-C RADAR ALTIMETER WILL HAVE SEVERAL FEATURES IN COMMON WITH THE ALTIMETER USED ON THE SKYLAB SATELLITE. BUT WILL HAVE ADVANTAGES OVER THE SKYLAB ALTIMETER BECAUSE OF ITS IMPROVED ACCURACY AND ABILITY TO OPERATE OVER EXTENDED AREAS FOR GREATER PERIODS OF TIMEs THEREBY PROVIDING THE CAPABILITY TO EXAMINE THE EARTH OVER LONGER ARCS AND OBSERVE EXTENSIVE OCEAN AREAS.

1008 ************GEOS-C. STECKEL

EXPERIMENT NAME- S-BAND TRANSPONDER SYSTEM NSSDC ID- GEOS-C -02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CThER INVESTIGATOR) PI - J.H. STECKEL NASA-GSFC GREENBELT, MD

EXPERIMENT BRIEF DESCRIPTION THE S-BAND-TRANSPONDER SUBSYSTEM WILL BE USED TO PROVIDE METRIC CAPABILITY OF TRACKING DATA (RANGE, RANGE-RATE). IT WILL NOT HAVE THE RECEIVING COMMANDS, BUT IT WILL HAVE THE CAPABILITY CF TRANSMITTING FOLLOWING THREE TELEMETRY DATA. THE TRANSPONDER WILL BE UTILIZED IN THE FROM THE ROSMAN PRIMARY MODES -- (1) SATELLITE-TO-SATELLITE TRACKING (SST) BACK, (2) DIRECT OR EUROPEAN ATS GROUND STATIONS THROUGH ATS-F TO GEOS-C AND AFTER THE USB GROUND USB (DOPPLER ONLY) GROUND STATION TRACKING OF GEOS-C. TRACKING OF STATIONS ARE MODIFIED, AND (3) DIRECT GRARR GROUND STATION SINGLE-CHANNEL GEOS-C. THE TRANSPCNDER SUBSYSTEM WILL CONSIST OF A AND TRANSPONDER, A POWER AMPLIFIER, AA DIPLEXER. AND AN EARTH-VIEWING ATS-VIEWING ANTENNA SYSTEM. THE ANTENNAS WILL BE SELECTABLE.BY GROUND THE USB AND COMMAND. THE EARTH-VIEWING ANTENNA FOR DIRECT TRACKING WITH COVERAGE AND A GRARR GROUNC STATIONS WILL HAVE APPROXIMATELY HEMISPHERICAL ANTENNA MINIMUM OF O-D GAIN WITHIN 60 DEG OF THE SPACECRAFT Z-AXIS. THE PROVIDE A 3-DB SYSTEM FOR SST WILL CONSIST OF AN IN-TRACK ARRAY WHICH WILL NODE PASSES, GAIN IN THE DIRECTION OF ATS FOR GEOS ASCENDING AND DESCENDING OF THE ATS WHICH WILL CROSS THE EQUATOR WITHIN PLUS OR MINUS 26 DEGREES SIGNAL SUB-SATELLITE POINT. IN THE SST MODE OF OPERATION, THE INTERROGATION TO THE ATS-F WILL FIRST BE TRANSMITTED AT C-BAND BY THE ATS GROUND STATION ALTER THE SPACECRAFT. ATS SPACECRAFT INSTRUMENTATION WILL COHERENTLY (2069.1125 MHZ) OF THE SIGNAL, MAKING IT COMPATIBLE WITH THE INPUT FREQUENCY GEOS-C. GEOS-C S-BAND TRANSPONDER ON GEOS-C. AND TRANSMIT THE SIGNAL TO IT TO ATS-F AS THEN, AFTER TRANSLATING THE RECEIVED SIGNAL WILL RETRANSMIT THE SIGNAL IF ATS-F WERE ANOTHER GROUND STATION. ATS-F WILL THEN RETRANSMIT SUM WILL BE TO THE ATS GROUND STATION AT C-BAND. RANGE SUM AND RANGE-RATE THE S-DAND OBTAINED BY COMPARING THE INTERROGATION AND RESPONSE SIGNALS. STDN STATIONS. SYSTEM ON GEOS-C WILL ALSO BE TRACKED BY THE USB AND GRARR WILL BE IDENTICAL CARRIER FREQUENCIES (2069.1125 MHZ UP, AND 2247 MHZ DOWN) VIA TO THOSE OF THE SST MODE. COHERENT GRARR TRACKING WILL BE ACCOMPLISHED ONLY OF STANDARD GRARR RANGING SIDE TONES. USB TRACKING WILL CONSIST WILL BE A COHERENT-CARRIER DOPPLER TRACKING. THE S-BAND TRANSPONDER OPERATION WILL NOT EE SINGLE-CHANNEL TRANSPONDER, AND THEREFORE SIMULTANEOUS POSSIBLE.

************GEOS-C, UNKNOWN

EXPERIMENT NAME- US NAVY DOPPLER SYSTEM NSSDC ID- GEOS-C -05

LAST REPORTED STATE- PRELAUNCH

INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER P1 - UNKNOWN UNKNOWN

EXPERIMENT BRIEF DESCRIPTION THE DOPPLER TECHNIQUE OF TIMING AND MEASURING THE FREQUENCY SHIFT OF TO OBTAIN DATA RADIO TRANSMISSIONS FROM A MOVING SPACECRAFT WILL BE USED

1009 WHICH WILL FURTHER ESTABLISH THE STRUCTLRE OF THE EARTH'S GRAVITATIONAL FIELD THROUGH THE COMPARISON OF NEW WITH ESTABLISHED GEODETIC MEASUREMENTS. TWO TRANSMITTERS WILL BE OPERATED AT FREQUENCIES OF 162 AND 324 MHZ. THE DUAL FREQUENCIES WILL BE COHERENTLY RELATED AND UTILIZED IN CONJUNCTION WITH GROUND DOPPLER RECEIVING STATIONS TO DEOTAIN PRECISION SATELLITE RANGE-RATE DATA. THE DUAL FREQUENCIES WILL BE GENERATED BY A HIGHLY STABLE OSCILLATOR DRIVING TWO FREQUENCY MULTIPLIERS. BOTH FREQUENCIES WILL BE USED SIMULTANEOUSLY TO PROVIDE COMPARISON DATA OF THE EFFECT OF THE IONOSPHERE CN THE SIGNALS. WHICH aILL THEN BE USED TO CORRECT THE DATA FOR THIS ERROR SOURCE. THIRTEEN OR MORE FIXED GROUND RECEIVING STATIONS OPERATED BY THE U.S. NAVY DOPPLER TRACKING NETWORK (TRANET) AND 12 PORTABLE GEOCEIVERS OPERATED BY THE U.S. ARMY, U.S. NAVY. AND U.S. AIR FORCE - ALL UNDER THE DIRECTION OF THE DEFENSE MAPPING AGENCY (DMA) - ARE EXPECTED TO BE IN OPERATION. OBSERVATIONS MADE FROM THREE OR MORE KNCWN STATIONS WILL ALLOW DEDUCTION OF ORBITAL PARAMETERS. RANGE-RATE DATA FROM EITHER THE FIXED STATIONS OR THE GEOCEIVERS IS ESTIMATED TO BE ACCURATE WITHIN 0.5 CM/SEC. DATA FROM THE SYSTEM WILL DE RECORDED ON PAPER TAFEs THEN REPRODUCED ON MAGNETIC TAPE FOR FURTHER PROCESSING.

*** *************** ****** *********************GMS

SPACECRAFT COMMON NAME- GMS ALTERNATE NAMES- GEOSTATION.METEOROL SAT. NSSDC ID- GMS

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 12/00/76 SPACECRAFT WEIGHT IN CRBIT- 250. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- THOR-DELTA

SPONSORING COUNTRY/AGENCY JAPAN NASDA JAPAN JMA

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 1440. MIN APOAPSIS- 36000. KM ALT PERIAPSIS- 36000. KM ALT INCLINATION- 0.0 DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - UNKNOWN NASDA TOKYOe JAPAN PS - UNKNOWN JMA TOKYO*JAPAN

SPACECRAFT BRIEF DESCRIPTION THE GEOSTATIONARY METEOROLOGICAL SATELLITE (GMS) WILL SERVE AS PART OF JAPAN'S CONTRIBUTION TO GARP (GLOBAL ATMOSPHERIC RESEARCH PROJECT). THE SPIN-STABILIZED SPACECRAFT WILL BE EQUIPPED WITH A VISUAL-INFRARED SENSOR TO PROVIDE NEAR-CONTINUOUS OBSERVATIONS OF VARIOUS WEATHER FEATURES. AS PART CF GARP, THE SATELLITE WILL HELP SUPPLY DATA REQUIRED FOR GLOBAL DATA SETSo TO BE USED I-N IMPROVEMENT OF MACHINE WEATHER FORECASTS. IN GENERAL, THE SPACECRAFT DESIGN, INSTRUMENTATION, AND OPERATION WILL BE SIMILAR TO SMS/GOES.

*****t* ***+#*#*+#####**,#### ***** *4*HCMMg4 4

SPACECRAFT COMMON NAME- HCMM ALTERNATE NAMES- SATS9 APPLICATIONS EXP MISSION, SMALL APPLICATIONS TECHe HEAT NSSDC ID- AEM-A

1010 LAST REPORTED STATE- A PROPOSED MISSION

PLANNED LAUNCH DATE- 03/00/77 SPACECRAFT WEIGHT IN CRBIT- '117. KG

LAUNCH SITE- VANDENEERG AFB, UNITED STATES LAUNCH VEHICLE- SCOUT-F

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OA

PLANNED ORBIT PARAMETERS ORdIT TYPE- GEOCENTRIC ORBIT PERIOD- 1440. MIN APOAPSIS- 600. KM ALT PERIAPSIS- 600. KM ALT INCLINATION- DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - P.G. MARCOTTE NASA-GSFC GREENBELT# MD PS - W.A. HOVIS NASA-GSFC GREENBELT* MD

SPACECRAFT BRIEF DESCRIPTION .THE OBJECTIVE OF THE HEAT CAPACITY MAPPING MISSION (HCMM) SPACECRAFT WILL BE TO PROVIDE COMPREHENSIVE, ACCURATE, HIGH SPATIAL RESOLUTION THERMAL SURVEYS OF THE SURFACE OF THE EARTH. THE SPACECRAFT WILL BE SPIN STABILIZEC AT A RATE OF 14 RPS. THE HCMM CIRCULAR SUN-SYNCHRONCUS ORBIT WILL BE CHOSEN TO ALLOW THE SPACECRAFT TO SENSE SURFACE TEMPERATURE NEAR THE MAXIMUM AND MINUMUM OF THE DIURNAL CYCLE. THE ORBIT WILL HAVE AN ASCENDING DAYLIGHT MOCE WITH NOMINAL EQUATORIAL CROSSING TIME OF 2 PM. AND WILL PROVIDE A ONE-THIRTY PM TO TWO-THIRTY AM CROSSING TIME OVER MIDDLE NORTHERN LATITUDES. THE ORBIT WILL ALSO ALLOW FOR REFLECTANCE MEASUREMENTS DURING DAYLIGHT PASSES.

************HCMM, HOVIS

EXPERIMENT NAME- HEAT CAPACITY MISSION RADICMETER NSSDC ID- AEM-A -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OT-ER INVESTIGATOR) PI - W.A. HOVIS NASA-GSFC GREENBELT, MD

EXPERIMENT BRIEF DESCRIPTION THE OBJECTIVES OF THE HEAT CAPACITY MAPPING RADIOMETER (HCMR) WILL BE AS FOLLOWS -- (1) TC PRODUCE THERMAL MAPS AT THE OPTIMUM TIMES FOR MAKING THERMAL INERTIA STUCIES FOR DISCRIMINATION OF ROCK TYFES AND MINERAL RESOURCES LOCATION, (2) TO MEASURE PLANT CANOPY TEMPERATURES AT FREQUENT INTERVALS TO DETERMINE THE TRANSPIRATION OF WATER AND PLANT LIFE, (3) TO MEASURE SOIL MOISTURE EFFECTS BY OBSERVING THE TEMPERATURE CYCLE OF SOILS. (4) TO MAP THERMAL EFFLUENTS, BOTH NATURAL AND MAN-MADE, (5) TO INVESTIGATE THE FEASIBILITY OF GEOTHERMAL SOURCE LOCATION BY REMOTE SENSING, AND (6) TC PROVIDE FREQUENT COVERAGE OF SNOW FIELDS FOR WATER RUNOFF PREDICTION. THE HCkR WILL TRANSMIT ANALOG DATA IN REAL TIME TO SELECTED RECEIVING STATIONS. IT IS DESIGNED TO PROVIDE ACCURATE, HIGH SPATIAL RESOLUTION THERMAL MAPS OF THE SURFACE OF THE EARTH AT AN OPTIMUM TIME TO DETERMINATION OF THERMAL INERTIA. THE HIGH THERMAL RESOLUTION DATA WILL ALSO BE USED TO MAP THERMAL GRADIENTS IN BOCIES OF WATER. THE RADIOMETER TO BE USED WILL BE SIMILAR TO THE HIGH-RESOLUTION SURFACE COMPOSITION MAPPING RADIOMETER (HRSCMR) OF NIMBUS 5 (72--097A). THE HCMR %ILL HAVE A SMALL INSTANTANEOUS GECMETRIC FIELD OF VIEW (LESS THAN 1 X 1 MILLIRADIANS), HIGH RADICMETRIC ACCURACY, AND A WIDE ENOUGH SWATH COVERAGE CN THE GROUND SO THAT SELECTED AREAS ARE COVEREC WITHIN THE 12-HR PERIOD CORRESPONDING TO THE MAXIMUM AND MINIMUM OF

1011 TEMPERATURE OBSERVED. THE INSTRUMENT WILL OPERATE IN TWO CHANNELS. 10.5 TO 12.5 MICROMETERS (IP) AND 0.8 TO 1.1 MICROMETERS (VISIBLE). THE LATTER CHANNEL WILL BE MATCHED TO THE ERTS-I (72-058A) BAND 4. THE INSTRUMENT IS TO UTILIZE A RADIATION COOLER TO COOL THE TWO HE-CD-TE DETECTORS TO 100 DEG K. THE EXPERIMENT WILL INCLUDE AN ANALOG MULTIPLEXER THAT WILL ACCEPT THE ANALOG OUTPUT OF EACH DETECTOR AND MULTIPLEX THEM IN A FORM SUITABLE FOR TRANSMISSION BY THE SPACECRAFT S-BAND TRAfSMITTER.

*****4~*~* 91***********#******~*** *HEAOA *******I* *

SPACECRAFT COMMON NAME- HEAO-A ALTERNATE NAMES- NSSDC ID- HEAO-A

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 1-ALF 77 SPACECRAFT WEIGHT IN CRBIT- 1090. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- ATLAS-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-CSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 410. KM ALT PERIAPSIS- 410. KM ALT INCLINATION- 22.5 DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - F.A. SPEER NASA HEADQUARTERS WASHINGTON# DC PS - F.B. MC DONALD NASA-GSFC GREENBELT. MD

SPACECRAFT BRIEF DESCRIPTION THE OBJECTIVE OF THE HIGH-ENERGY ASTRONOMY OBSERVATORIES WILL BE TO CONDUCT COORDINATE RESEARCH INTO X-RAY AND GAMMA-RAY ASTRONOMY AND COSMIC-RAY ASTROPHYSICS. THE HEAO SPACECRAFT WILL BE DESIGNED TO CARRY THE LARGE AND HEAVY SCIENTIFIC INSTRUMENTATION REQUIRED TO CONDUCT CBSERVATIONS AT THE VERY-HIGH-ENERGY AND LOW-FLUX LEVELS OF THESE PHENOMENA. THE PRIME OBJECTIVE OF THIS MISSION WILL EE TO CONDUCT AN X-RAY SKY SURVEY.

************HEAC-A, BOLDT

EXPERIMENT NAME- CCSMIC X-RAY EXPERIMENT NSSDC ID- HEAO-A -02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - E.A. BOLDT NASA-GSFC GREEN8ELT, MD 01 - G.P. GARMIRE CAL TECH PASADENA, CA OI - C.S. BOWYER U CALIFCRNIA, BERK BERKELEY, CA 01 - R. CRUDDANCE U CALIFORNIA. BERK BERKELEY* CA 01 - G.B. FIELD SAO CAMBRIDGE, MA OI - M.L. LAMPTON U CALIOCRNIA. BERK BERKELEY, CA OI - J.I. SILK U OF CALIFCRNIA, BERK BERKELEY, CA OI - S.S. HOLT NASA-GSFC 'GREENBELT, MD OI - P.J. SERLEMITSOS NASA-GSFC GREENBELT, MD UI - G.R. RIEGLER BENDIX CORP ANN ARBOR, MI

1012 EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL BE USED TO MAP THE X-RAY SKY IN THE RANGE FROM C.2 TO 6- KEV, EMPHASIZING BRIGHTNESS DISTRIBUTION OF THE DIFFUSE BACKGROUND, CORRELATION OF GALACTIC RADIO EMISSION AND X-RAY EMISSION FROM COSMIC RAY ELECTRONS, AND RELATIVE EMISSION AND ABSORPTION BY INTERSTELLAR MATTER. SIX THIN-WINDOW PROPORTIONAL COUNTERS COVERING THE RANGES FROM 0.2 TO 4 KEV, 1.5 TO 15 KEV, AND 3 TO 60 KEV, AND COLLIMATED TO FIELDS OF VIEW OF 1.5 X 3 DEG, 3 X 3 DEG, OR 3 X 6 DEG, WILL BE USED. THE TOTAL DETECTOR AREA WILL BE 1.32 M SQ.

************HEAC-A, FRIEDMAN

EXPERIMENT NAME- LARGE AREA COSMIC X-RAY SURVEY NSSDC ID- HEAO-A -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - H.D. FRIEDMAN NAVAL RESEARCH LAd WASHINGTON. DC OI - T.A. CHUBB NAVAL RESEARCH LAB WASHINGTOCh DC 01 - E.T. BYRAM NAVAL RESEARCH LAB WASHINGTON, DC 0I - G.G. FRITZ NAVAL RESEARCH LAB WASHINGTON, DC 01 - J.F. MEEKINS NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPEPIMENT WILL MAP THE X-RAY SKY FROM 0.15 TO 20 KEV WITH HIGH SENSITIVITY AND MODERATE ANGULAR AND ENERGY RESOLUTION TO LOCATE X-RAY SOURCES WITH SUFFICIENT ACCURACY AND TO DETERMINE THE NATURE AND EXTENT OF BOTH GALACTIC AND EXTRAGALACTIC SOURCES. SIX PROPCRTIONAL COUNTER MODULES WILL BE USED. WITH COLLIMATIONS OF I X 4 DEG, 1 X 0.5 DEG. OR 2 X 8 DEG, DEPENDING UPON THE MODULE.

************HEAC-As GURSKY

EXPERIMENT NAME- X-RAY SCANNING MODULATION CCLLIMATOR NSSDC ID- HEAO-A -03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR.) P1 - H. GURSKY HARVARD COLLEGE OBS CAMBRIDGE. MA Ol - H. BRADT MIT CAMBRIOGE, MA 01 - G.W. CLARK MIT CAMBRIDGE. MA oI - W*H.G. LEWIN MIT CAMBRIDGE, MA OI - S. RAPPAPORT MIT' CAMBRIDGE, MA OI,- G. SPADA MIT CAMBRIDGE MA aO - R. DOXSEY MIT CAMBRIDGE, MA Ol - R. GIACCONI HARVARD COLLEGE OBS CAMBRIDGE. MA OI - P. GORENSTEIN HARVARD COLLEGE OBS CAMBRIDGE. MA OI - E.M. KELLOGG HARVARD CCLLEGE OUS CAMBRIDGE* MA OI - H. TANENBAUM HARVARD COLLEGE CBS CAMBRIOGE, MA oI - D. SCHWARTZ AS+E CAMBRIDGE, MA

EXPERIMENT BRIEF DESCRIPTION THE OBJECTIVES OF THIS EXPERIMENT WILL BE (1) TO DETERMINE THE CELESTIAL POSITIONS OF COSMIC X-RAY SOURCES TO A PRECISION OF ABOUT 5 ARC-SEC. (2) TO CETERMINE THE ANGULAR SIZE OF COSMIC X-RAY SOURCES TO A PRECISION OF ABOUT 5 TO 10 ARC-SEC IN THE ENERGY RANGE FROM 1.0 TO 15 KEV, AND (3) TO STUDY THE STRUCTURE OF THE X-RAY EMISSION TO A PRECISION OF 10

1013 ARC-SEC IN THE ENERGY RANGE FROM I.C TO 15 KEV. THE EXPERIMENT WILL CONSIST OF TwC INDEPENDENT MODULATION CGLLIMATOR BANKS TO SCAN THE CELESTIAL SPHERE IN THE Y-DIRECTION. EACH BANK WILL HAVE A SERIES OF FOUR WIRE GRIDS. WHIC- WILL FORM A SERIES OF TRIANGULAR ACCEPTANCE PATTERNS. THE FWHM OF THE TRIANGULAR RESOLUTION ELEMENTS WILL BE 30 ARC-SEC FOR ONE COLLIMATOR BANK AND 12- ARC-SEC FOR THE OTHER. IN ADDITION, EACH BANK WILL HAVE AN EGG-CRATE COLLIMATOR TO LIMIT THE VIEW TO 4-DEG X 8-DEG FWHM. THERE WILL EE FOUR SEALED PROPORTIONAL COUNTERS ASSOCIATED WITH EACH BANK. THE COUNTERS WILL HAVE 25-MICRON GERYLLIUM WINDOWS AND WILL BE FILLED WITH A MIXTURE OF O0-PERCENT ARGON AND 13-PERCENT CARBON DIOXIDE TO A PRESSURE SLIGHTLY GREATER THAN 1 ATM.

************HEAO-A PETERSON

EXPERIMENT NAME- LOW-ENERGY GAMMA-RAY SKY SLRVEY NSSOC 10- HEAO-A -04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATCR) PI - L.E. PETERSCN U OF CALIFCRNI[A SO SAN DIEGO. CA OI - W.H.G. LEWIN MIT CAMBRIDGE. MA OI - R.M. PELLING U OF CALIFORNIA, SO LA JOLLA, CA OI - J.L. MATTESON U OF CALIFCRNIA. SD LA JOLLA* CA 01 - A. SCHEEPMAKER U OF CALIFCRNIA. SD LA JOLLA. CA OI - H. BRADT MIT CAMBRIDGE, MA 01 - G.W. CLARK MIT CAMBRIDGE# MA OI - S. RAPPAPOPT MIT CAMBRIDGE, MA

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THIS EXPERIMENT WILL BE TO SEARCH THE CELESTIAL SPHERE FOR PHENOMENA IN THE ENERGY RANGE FROM 0.01 TO 10 MEV. THE SEARCH WILL BE ORIENTED TO THE GATHERING OF DATA WITHIN TWO DISTINCT ENERGY BANDS - 10 TO 200 KEV, AND C.1 TO 10 MEV. WITHIN THE 10- TO 200-KEV REGICN. EMPHASIS WILL LE PLACED ON THE FOLLOWING TYPE OF STUDIES. DETERMINATIONS WILL BE MADE OF THE INTENSITY AND SPECTRA OF POINT X-RAY SOURCES. AT A SENSITIVITY OF 7E-4 PHOTONS/CM SQ/SEC. STUDIES WILL BE MADE TO FIX THE POSITIONS OF STRONG SOURCES (1.6E-2 PHOTONS/CM SO/SEC OR MORE) TO 0.1 DEGREE. AND TO ABOUT 1 DEG FOR THRESHOLD SOURCES. SEARCHES WILL BE MADE FOR TRANSIENT SOURCES. ALL PERIODIC AND NON-PERIODIC TIME VARIATIONS IN ANY SOURCE ENCOMPASSED BY THIS INVESTIGATION WILL BE AT A TIME RESOLUTION OF APPROXIMATELY 50 MICRO-SECONDS. WORK IN THE 0.1- TO 10-MEV RANGE WILL ADDRESS THREE FUNDAMENTAL STUDIES -- (1) MEASUREMENT OF THE SPECTRUM AND ISOTROPY OF THE DIFFUSE AND THE GALACTIC GAMMA RAYS. (2) MEASUREMENT OF THE SPECTRUM AND TIME VARIATIONS OF STRONG GALACTIC AND EXTRAGALACTIC POINT SOURCES AND. (3) DETERMINATION OF VARIOUS BACKGROUND COMPONENTS AND PRODUCTION EFFECTS NEEDED TO INTERPRET THE ABOVE DATA, AND TO PROVIDE INFORMATION FOR FUTURE MISSIONS SUCH AS THE SHUTTLE. THE EXPERIMENTAL PACKAGE WILL CONTAIN SEVEN PHOSWICH DETECTORS. SHIELDED BY ACTIVE COLLIMATOR ANTICOINCIDENCE CRYSTALS. TO RECORD THE ENERGETIC PHOTONS IN THE ENERGY RANGE FRCM 0.01 TO 10 MEV. ONE DETECTCR WILL BE COLLIMATED WITH A 2-DEG SLOT COLLIMATOR TO GIVE HIGH ANGULAR RESOLUTION AT THE LOW ENERGIES. ITS FIELD OF VIEW WILL BE 2 BY 20 DEG. THE OTHER DETECTORS WILL HAVE A FIELD OF VIEW OF 20 BY 40 DEG. A CESIUM IODIDE BLOCKING CRYSTAL WILL BE POSITIONED OVER THE APERTURE OF A DETECTOR TO RECORD THE BACKGROUND EVENTS IN THE DETECTOR.

*****************************************HEAO ********

1014 SPACECRAFT COMMON NAME- HEAO-B ALTERNATE NAMES- NSSDC ID- HEAO-B

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 2HALF 78 SPACECRAFT WEIGHT IN CRBIT- 1270. KG

LAUNCH SITE- CAPE KENNEDY. UNITED STATES LAUNCH VEHICLE- ATLAS-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-CSS

PLANNED ORIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN 22.5 DEG APDAPSIS- 435. KM ALT PERIAPSIS- 435. KM ALT INCLINATION-

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - F.A. SPEER NASA HEADQUARTERS WASHINGTON, DC PS - S.S. HOLT NASA-GSFC GREENBELT, MD

SPACECRAFT BRIEF DESCRIPTION THE OBJECTIVE OF THE HIGH-ENERGY ASTRONOMY OBSERVATORIES WILL BE TO AND CONDUCT COORDINATED RESEARCH INTO X-RAY AND GAMMA-RAY ASTRONOMY COSMIC-RAY ASTROPHYSICS. THE HEAD SPACECRAFT WILL BE DESIGNED TO CARRY THE LARGE AND HEAVY SCIENTIFIC INSTRUMENTATICN REQUIRED TO CONDUCT CBSERVATIONS AT THE VERY-HIGH-ENERGY AND LOW-FLUX LEVELS OF THESE PHENOMENA. THIS MISSION WILL UTILIZE A POINTED X-RAY TELESCOPE.

***********#HEAC-B, BOLDT

EXPERIMENT NAME- SOLID-STATE X-RAY DETECTOR NSSDC ID- HEAO-B -05

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) MD PI - E. BOLDT NASA-GSFC GREENBELT,

EXPERIMENT BRIEF DESCRIPTION THIS INSTRUMENT WILL BE A COOLED SOLID-STATE SPECTRCMETER AND WILL BE OF USED TO DETECT WEAK SOURCES AND WEAK SPECTRAL FEATURES OVER A BROAD BAND ENERGIES BY EMPLOYING A NONDISPERSIVE SPECTRAL TECHNIQUE. A LITHIUM-DRIFTED THE SOLID-STATE DETECTOR WILL BE OPERATED AT A TEMPERATURE OF 120 DEG K. VETO PRIMARY DETECTOR WILL BE 6 MM IN DIAMETER AND WILL eE SURROUNDED BY TWO TO COCL GUARD COUNTERS. A TWO-STAGE SOLID CRYOGEN REFRIGERATOR WILL BE USED THE UETECTOR. SPECTRAL MEASUREMENTS WILL BE MADE EETWEEN 0.5 AND 4 KEV, WITH A RESOLUTION FROM 120 TO 15C EV, FWHM AND AN EFFICIENCY GREATER THAN 0.9.

************HEAC-8, CLARK

EXPERIMENT NAME- A CURVED-CRYSTAL BRAGG X-RAY SPECTROMETER NSSDC ID- HEAO-8 -03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR)

Ic 15 PI - G.W. CLARK MIT CAMBRIDGE, NA

EXPERIMENT BRIEF DESCRIPTION THE OVJECTIVE OF THIS EXPERIMENT WILL BE TO SEARCH FOR X-RAY SPECTRAL LINE EMISSIONS ARISING FROM THE SELECTED CELESTIAL OBJECTS. THE SEARCH WILL BE LIMITED TO THE ENERGY LEVEL FROM 0.1 TO 3 KEV. THE INSTRUMENT WILL BE A CURVED-CRYSTAL ERAGG SPECTROMETER USING SIX CRYSTALS. THE SELECTION OF SPECIFIC CRYSTALS WILL BE MADE FROM AMONG PET, ADP, BERYL RAP, LEAD LAURATEs AND LEAD STEARATE. THE SPECTROGRAPH RESOLUTION WILL DEPEND ON THE FINAL SELECTION OF CRYSTALS. RAP AND ADP WOULD GIVE RESOLUTIONS IN LAMBDA/DELTA-LAMBDA OF GREATER THAN 2500. LEAD STEARATE AND LAURATE WOULD GIVE RESOLUTICNS OF APPROXIMATELY 10,. THE X-RAY LINES WILL DE DETECTED BY A THIN-WINDOW POSITION-SENSITIVE PROPORTIONAL COUNTER.

************HEAC-E, GIACCCNI

EXPERIMENT NAME- MCONITOR PROPORTIONAL COUNTER NSSDC ID- HEAO-B -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTFER INVESTIGATOR) PI - R. GIACCONI HARVARD COLLEGE OOS CAMBRIDGE, MA

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE A MCNITOR COUNTER AS A SUPPORT INSTRUMENT FOR CALIBRATION AND NORMALIZATION OF THE FOCAL PLANE INSTRUMENTATION. IT WILL BE USED TC (1) NORMALIZE INTENSITY FLUCTUATIONS DURING SPECTROMETER OBSERVATIONS, (2) OBSERVE THE CONTINUUM DURING SPECTRAL LINE CBSERVATIONS, AND (3) CALIERATE CERTAIN INSTRUMENTS IN FLIGHT.

**l*********HEAC-Be GIACCCNI

EXPERIMENT NAME- HIGH RESOLUTION IMAGER NSSDC ID- HEAO-B -02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R. GIACCONI HARVARD COLLEGE ODS CAMBRIDGE* MA

EXPERIMENT BRIEF DESCRIPTION THE OBJECTIVES OF THIS EXPERIMENT WILL BE TO (1) DETECT AND ACCURATELY LOCATE X-RAY SOURCES IN THE ENERGY RANGE FROM 0.2 TO 4 KEV, (2) STUDY THE STRUCTURE OF OBJECTS LARGER THAN 2 ARC-SEC. AND (3) MEASURE THE INTENSITY AND TEMPORAL CFARACTERISTICS OF INDIVIDUAL POINT SOURCES.

************HEAO-Be GURSKY

EXPERIMENT NAME- IMAGING PROPORTIONAL COUNTER NSSDC I0- HEAO-B -04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - H. GURSKY HARVARD COLLEGE OBS CAMBRIDGE, MA

EXPERIMENT BRIEF DESCRIPTION

1016 THE OBJECTIVES OF THIS EXPERIMENT WILL BE -- (1) TO SURVEY X-RAY SOURCES OF AN EXTENDED NATURE IN THE ENERGY RANGE FROM 0.1 TO 4 KEV, WHERE RESOLUTION OF 1 ARC-MIN WILL BE SUFFICIENT. (2) TO STUDY THE ANGULAR STRUCTURE OF EXTENDED SOURCES, (3) TO SURVEY FOR WEAK SCURCES, AND (4) TO LOCATE OBJECTS WITH POORLY KNCWN POSITIONS.

************** *******4*********************HE- ***********

SPACECRAFT COMMON NAME- HEAO-C ALTERNATE NAMES- NSSOC 10- HEAO-C

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 2HALF 79 SPACECRAFT WEIGHT IN ORBIT- 1090. KG

LAUNCH SITE- CAPE KENNEDY. UNITED STATES LAUNCH VEHICLE- ATLAS-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 480. KM ALT PERIAPSIS- 480. KM ALT INCLINATION- 50. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - F.A. SPEER NASA-MSFC HUNTSVILLE, AL PS - T.A. PARNELL NASA-MSFC HLNTSVILLE, AL

' SPACECRAFT BRIEF DESCRIFTION THE OBJECTIVE OF THE HIGH-ENERGY ASTRONOMY OBSERVATORIES WILL BE TO CONDUCT COORDINATED RESEARCH INTO X-RAY AND GAMMA-RAY ASTRONOMY AND COSMIC-RAY ASTROPHYSICS. THE HEAO SPACECRAFT WILL BE DESIGNED TO CARRY LARGE AND HEAVY SCIENTIFIC INSTRUMENTATION REQUIREC TO CONDUCT OBSERVATIONS AT THE VERY-HIGH-ENERGY AND LOW-FLUX LEVELS OF THESE PHENOMENA. THIS MISSION WILL EMPHASIZE GAMMA-RAY ASTRONCMY AND COSMIC-RAY ASTROPHYSICS.

*****+*******HEAC-C, ISRAEL

EXPERIMENT NAME- HEAVY NUCLEII EXPERIMFNT NSSDC 10- HEAO-C -03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTI-ER INVESTIGATOR) LOUIS. MO PI - M.H . ISRAEL WASHINGTON U ST. CA PI - E.C. STONE CAL TECH PASADENA, MI PI - C.J. WADDINGTON U OF MINNESOTA MINNEAPCLIS. ST. LOUIS, MO DI - W.R. BINNS MCCONNELL 'DCLGLAS LCUIS, MO 01 - J. KLARMANN WASHINGTON U ST. CA Ol - R.E. VOGT CAL TECH PASADENA,

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THIS EXPERIMENT WILL BE TO MEASURE THE CHARGE SPECTRUM 120 IN THE oF COSMIC-RAY NUCLEI OVER THE NUCLEAR CHARGE RANGE FROM 17 TO SOURCES, ENERGY INTERVAL 0.3-TO 10-GEV/NUCLEON TO CHARACTERIZE COSMIC RAY CONSIST PROCESSES OF SYNTHETICS, AND PROPAGATION MODES. THE DETECTOR WILL OF A DOUBLE-ENDED INSTRUMENT OF UPPER AND LOWER HCDCSCOPES AND THREE DUAL-GAP ION CHAMBERS. THE TwO ENDS WILL BE SEPARATED EY A CERENKOV

1017 RADIATOR. THE GEOMETRICAL FACTOR WILL BE A 4 SO-M STER. THE ICN CHAMBERS CAN RESOLVF CHARGE TO 0.24-CHARGE UNITS AT LOW ENERGY AND 0.39-CHARGE UNITS AT HIGH ENERGY AND hIGH Z. THE CERENKOV COUNTER CAN RESOLVE 0.3-TO J.4-CHARGE UNITS.

************HEAC-C, JACOBSON

EXPERIMENT NAME- GAMMA RAY LINE SPECTROMETER NSSDC IO- HEAO-C -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - A.S. JACOBSON NASA-JPL PASADENA, CA OI - J.R. ARNOLD U OF CALIFCRNIA, SD LA JCLLA. CA 01 - A.E. METZGER NASA-JPL PASADENA. CA 01 - L.t- PETERSCN U OF CALIFCRNIA, SD LA JOLLA, CA

EXPERIMENT BRIEF DESCRIPTION THE BASIC GOALS OF THIS EXPERIMENT WILL BE TO SEARCH FOR GAMMA-RAY LINE EMISSIONS ARISING FROM A VARIETY CF SOURCE PHENOMENA. PARTICULAR EMPHASIS WILL eE PLACED ON FINDING LINE EMISSIONS FROM NUCLEOSYNTHESIS PROCESSES IN SUPERNCVAE, AND FROM POSITRON-ELECTRON ANNIHILATION AND NUCLEAR REACTIUNS IN LOW-ENERGY COSMIC RAYS. IN ADDITION. CAREFUL STUDY WILL BE MADE OF THE SPECTRA AND TIME VARIATIONS OF KNOWN HARD X-RAY SOURCES. THE EXPERIMENT WILL BE CAPABLE OF MEASURING GAMMA-RAY LINES FALLING WITHIN THE ENERGY INTERVAL FROM 0.06 TO 10 MEV, AND WITH AN ENERGY RESOLUTION BETTER THAN 2.5 KEV AT 1.33 MEV AT A LINE SENSITIVITY FROM IE-4 TO IE-5 PHOTONS/CM SQ/SEC. DEPENDING ON THE ENERGY. THE EXPERIMENTAL PACKAGE WILL CONTAIN FOLR COOLED DRIFTED GERMANIUM DETECTORS SHIELDED BY CESIUM IODIDE. THE KEY EXPERIMENTAL PARAMETERS WILL BE -- (1) GECMETRY FACTOR OF 11.1 SQ-CM STER, (2) A FIELD OF VIEW OF 27 DEG FWHM AND, (3) A TIME RESOLUTION OF LESS THAN 0.1 MSEC FOR THE GERMANIUM DETECTOR AND 10 SEC FOR THE CESIUM IODIDE DETECTOR.

************HEAO-C, KOCH

EXPERIMENT NAME- ISCTOPIC COMPOSITION OF COSMIC RAYS NSSDC ID- HEAO-C -04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTFER INVESTIGATOR) PI - L. KOCH CEN SACLAYP FRANCE PI - B. PETERS DANISH INST SPACE RSCH LYNGBY, DENMARK 01 - J.P. MEYER CEN SACLAY. FRANCE 01 - D. ROUSSEL CEN SACLAY, FRANCE OI - A. SOUTOUL CEN SACLAY, FRANCE OI - M. CASSE CEN SACLAY. FRANCE 01 - P. MESTREAU CEN SACLAY, FRANCE 01 - N. LUND DANISH INST SPACE RSCH LYNGBY, DENMARK 01 - K. OMO DANISH INST SPACE RSCH LYNGBY,,DENMARK OI - 0. CORYDON-PETERSON DANISH INST SPACE RSCH LYNGBY, DENMARK

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL MEASURE THE RELATIVE COMPOSITION OF THE ISOTOPES OF THE PRIMARY COSMIC RAYS EETwEEN BERYLLIUM AND IRON (Z FROM 4 TO 26) AND THE ELEMENTAL ABUNDANCES UP TO TIN (Z=50). CERENKOV COUNTERS AND HODOSCOPES WILL BE COUPLED WITH THE EARTH'S MAGNETIC FIELD TC BE USED AS A

1018 SPECTROMETER. THEY WILL DETERMINE CHARGE AND MASS OF COSMIC RAYS TO A PRECISION OF 10 PERCENT FOR THE MOST ABUNDANT ELEMENTS OVER THE MOMENTUM RANGE FROM 2 TO 25 GEV/C.

************HEAC-C, MEYER

EXPERIMENT NAME- PRIMARY COSMIC RAY ELECTRONS NSSDC IO- HEAO-C -05

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - P. MEYER U OF CHICAGO CHICAGO, IL OI - J.E. LAMPORT U OF CHICAGO CHICAGO, IL OI - D. MULLER U OF CHICAGO CHICAGO, IL

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT IS DESIGNED TO DETERMINE THE COSMIC-RAY ELECTRON SPECTRUM FROM 5 TO 1,000 GEV TO GAIN INFORMATION ON THE ENERGY DENSITY OF MAGNETIC AND PHOTON FIELDS IN INTERSTELLAR SPACE, THE DISTANCE TO THE ELECTRON SOURCE, AND THE TIME SINCE THE PRODUCTION OF THE ELECTRONS. A DOUBLE ENDED TELESCOPE USING A TUNGSTEN-SCINTILLATOR SANDWICH WILL BE USED. THE ARRANGEMENT WILL BE DOUBLE-ENDED AND HAVE A GEOMETRIC FACTOR OF 900 SQ-CM STER. AND AN ENERGY RESCLUTION OF 25 PERCENT. COMPOSITION STUDIES OF CARBON, NITROGEN, OXYGEN, IRON, AND MANGANESE ABOVE 3000 GEV/NUC WILL ALSO BE PERFORMED.

**********************************************INTERCOSMOS 10 **

SPACECRAFT COMMON NAME- INTERCOSMOS 10 ALTERNATE NAMES- 6911 NSSDC ID- 73-082A

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNOWN DATA ACQUISITION RATE SINCE 10/30/73.

LAUNCH DATE- 10/30/73 SPACECRAFT WEIGHT IN ORBIT- 550. KG

LAUNCH SITE- LAUNCH VEHICLE- UNDISC

SPONSORING COUNTRY/AGENCY U.S.S.R. UNKNOWN

INITIAL ORBIT PARAMETERS EPOCH DATE- 10/31/73 ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 102. MIN APOAPSIS- 1477. KM ALT PERIAPSIS- 265. KM ALT INCLINATION- 74. DEG

RECENT ORBIT PARAMETERS EPOCH DATE- 10/31/73 ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 102. MIN APOAPSIS- 1477. KM ALT PERIAPSIS- 265. KM ALT INCLINATION- 74. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - UNKNOWN UNKNOWN PS - UNKNOWN UNKNOWN

SPACECRAFT BRIEF DESCRIPTION THE MAIN SCIENTIFIC OBJECTIVE OF THIS SATELLITE WAS TO STUDY MAGNETOSPHERE-IONOSPHERE COUPLING. THE SPIN RATE OF THE SATELLITE WAS LESS THAN OR EQUAL TO ONE REVOLUTION EVERY FIVE MINUTES. DATA WERE TRANSMITTED

1019 BOTH IN REAL TIME AND IN TAPE-RECORDER MODE. THE SCIENTIFIC EXPERIMENTS ON BOARD THE SATELLITE INCLUDED MEASUREMENTS OF ELECTRIC AND MAGNETIC FIELD FLUCTUATIONS, CF LOW-ENERGY PARTICLE FLUXES, OF PLASMA CONCENTRATION AND TEMPERATURE, ANC OF VLF EMISSIONS.

************INTERCOSMOS 10, UNKNOWN

EXPERIMENT NAME- MAGNETIC FIELD MEASUREMENT NSSDC ID- 73-082A-01

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNCWN DATA ACQUISITION RATE SINCE 10/30/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) Pl - UNKNOWN UNKNOWN OI - UNKNOWN UNKNOWN

EXPERIMENT BRIEF DESCRIPTION A THREE-CCMPONENT FLUX-GATE MAGNETOMETER WITH A FIELD-ALIGNED SERVO SYSTEM WAS USED FOR MEASURING THREE COMPONENTS OF VARIATIONS OF THE EARTH'S MAGNETIC FIELD INDUCTION VECTOR DELTA 8. THE DYNAMIC RANGE OF THE MEASUREMENTS WAS 600 GAMMAS.

************INTERCOSMOS 10. UNKNOWN

EXPERIMENT NAME- ELECTRIC FIELD MEASUREMENT NSSDC ID- 73-082A-02

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNOWN DATA ACQUISITION RATE SINCE 10/30/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - UNKNOWN UNKNOWN OI - UNKNOWN UNKNOWN

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT MEASURED ELECTRIC FIELD FLUCTUATIONS USING A DOUBLE-PROBE TECHNIGUE AND OPERATING IN THE FREQUENCY RANGE FROM 0.03 TO 70 HZ.

************INTERCOSMOS 10 UNKNOWN

EXPERIMENT NAME- LOW-ENERGY PARTICLES NSSDC ID- 73-082A-03

LAST REPORTED STATE- LAUNCHED AND OPERATING-NORMALLY AT AN UNKNOWN DATA ACQUISITION RATE SINCE 10/30/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - UNKNOWN UNKNOWN 01 - UNKNOWN UNKNOWN

EXPERIMENT BRIEF DESCRIPTION AN ELECTRCN AND PROTON SPECTROMETER WAS FLOWN TO MEASURE LOW-ENERGY PARTICLES IN THE ENERGY RANGES FROM 0.5 TO 5.0 KEV AND 0.05 TO 20 KEV. THE WHOLE RANGE WAS DIVIDED INTO 32 SUBRANGES. THE ENERGY RESOLUTION WAS APPROXIMATELY 5 PERCENT.

1020 ************INTERCOSMOS 10s UNKNOWN

EXPERIMENT NAME- VLF EMISSIONS NSSOC ID- 73-082A-04

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNOWN DATA ACQUISITION RATE SINCE 10/30/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - UNKNOWN UNKNOWN 01 - UNKNOWN UNKNOWN

EXPERIMENT BRIEF DESCRIPTION THE FREQUENCY RANGE OF THE BROADBAND CHANNEL WAS FROM 22 TO 22,000 HZ. THE DYNAMIC RANGE WAS 80 DECIBELS.

******t****INTERCOSMOS 10, UNKNOWN

EXPERIMENT NAME- ELECTRON CONCENTRATION AND TEMPERATURE NSSDC ID- 73-082A-C5

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNOWN DATA ACQUISITION RATE SINCE 10/30/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=COTER INVESTIGATOR) PI - UNKNOWN UNKNOWN OI - UNKNOWN UNKNCWN

EXPERIMENT BRIEF DESCRIPTION A LANGMUIR PROBE WAS USED TO MEASURE ELECTRON CONCENTRATION AND TEMPERATURE.

***+*+*#* #**********t************S *************

SPACECRAFT COMMON NAME- ISEE-A ALTERNATE NAMES- IMP-K, IME-M, MOTHER NSSDC ID- MOTHER

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 2HALF 77 SPACECRAFT WEIGHT IN ORBIT- 270. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-CSS INTERNATIONAL ESRO

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERICD- MIN APOAPSIS- 131000. KM ALT PERIAPSIS- 500. KM ALT INCLINATION- 28. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - J.J. MADDEN NASA-GSFC GREENBELT, MD PS - J.H. TRAINOR NASA-GSFC GREENBELT, MD PS - K. OGILVIE NASA-GSFC GREENBELT, MD

1021 SPACECRAFT BRIEF DESCRIPTION THE EXPLORER CLASS MOTHER SPACECRAFT WILL BE PART OF THE MOTHER/DAUGHTER/HELIOCENTRIC MISSION. THE PURPOSES CF THE MISSION WILL BE -- (1) TO INVESTIGATE SOLAR/TERRESTRIAL RELATIONSHIPS AT THE OUTERMOST BOUNDARIES OF THE EARTH'S MAGNETOSPHERE, (2) TO EXAMINE IN DETAIL THE STRUCTURE OF THE SOLAR WIND NEAR THE EARTH AND THE SHOCK WAVE THAT FORMS THE INTERFACE BETWEEN THE SOLAR WING AND EARTH, AND (3) TO CONTINUE THE INVESTIGATION OF COSMIC RAYS AND SOLAR FLARES IN THE INTERPLANETARY REGION NEAR I AU. THE MISSION WILL THUS EXTEND THE INVESTIGATIONS OF PREVIOUS IMP SPACECRAFT. THE MOTHER/DAUGHTER PORTION OF THE MISSION WILL CONSIST OF TWO SPACECRAFT WITH A STATION-KEEPING CAPABILITY IN A HIGHLY ECCENTRIC EARTH ORBIT WITH APOGEE FROM 18 TO 23 EARTH RADII. THE SPACECRAFT WILL MAINTAIN A SMALL SEPARATION DISTANCE, AND WILL MAKE SIMULTANEOUS COORDINATED MEASUREMENTS TC PERMIT SEPARATION OF SPATIAL FROM TEMPORAL IRREGULARITIES IN THE NEAR-EARTH SOLAR WIND. THE BOW SHOCK, AND INSIDE THE MAGNETCSPHERE.

************ISEE-A, HARVEY

EXPERIMENT NAME- ACTIVE PLASMA EXPERIMENT NSSDC ID- MOTHER -08

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - C.C. HARVEY PARIS OBSERVATORY MEUDON, FRANCE 01 - M. PETIT CNET PARIS, FRANCE OI - J.R. MCAFEE NOAA BOULDER, CO OI - D. JONES EUR SPACE TECH CENTER NCORDWIJK, THE NETHERLANDS 01 - J.M. ETCHETO CNET PARIS, FRANCE 01 - R.J.L. GRARD EUR SPACE TECH CENTER NOORDWIJK, THE NETHERLANDS OI - R. GENDRIN CNET PARIS, FRANCE

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL MEASURE THE PLASMA ELECTRON DENSITY NEAR THE MOTHER SATELLITE AND ALSO THE TOTAL ELECTRON CONTENT BETWEEN THE MOTHER ANC DAUGHTER SPACECRAFT. THE EXPERIMENT WILL CONSIST OF TWO DISTINCT PARTS -- (I) THE MOTHER SPACECRAFT WILL CARRY AN EXPERIMENT TO DETECT RESONANCES OF THE AMBIENT PLASMA. AFTER AN ANTENNA HAS BEEN MOMENTARILY EXCITED AT ONE OF THE CHARACTERISTIC FREQUENCIES OF THE PLASMA IN WHICH IT IS IMMERSED, A PRONOUNCED 'RINGING' WILL BE OBSERVED. THESE RESONANCES OCCUR AT THE PLASMA FREQUENCY, THE UPPER HYBRID RESONANCE, THE CYCLOTRON FREQUENCY AND ITS HARMONICS. ANC THE MEASUREMENT OF THEIR FREQUENCIES WILL PERMIT THE DETERMINATION OF SEVERAL PLASMA PARAMETERS, INCLUDING THE ELECTRON DENSITY. IN THIS EXPERIMENT, THE TRANSMITTER WILL BE DESIGNED TO STEP THROUGH A NUMBER OF SUB-BANDS, COVERING THE CHARACTERISTIC RESONANCE FREQUENCIES OF THE PLASMA, AND (2) THE INTEGRATED DENSITY BETWEEN THE MOTHER AND THE DAUGHTER WILL EE OBTAINED FROM A SECOND EXPERIMENT WHICH WILL MEASURE THE PHASE DELAY INTRODUCED BY THE AMBIENT PLASMA. ONTO A WAVE OF FREQUENCY ABOUT 1 MHZ TRANSMITTED FROM THE MOTHER AND RECEIVED ON THE DAUGHTER (EXPERIMENT 6). THE PHASE WILL BE COMPARED AGAINST A PHASE-COHERENT SIGNAL TRANSMITTED FROM THE MOTHER TO THE DAUGHTER BY MODULATION ONTO A CARRIER OF FREQUENCY HIGH ENOUGH TO BE UNAFFECTED BY THE AMBIENT PLASMA.

************ISEE-A, MOZER

EXPERIMENT NAME- DC TO 12-HZ ELECTRIC FIELD PROBE NSSDC ID- MOTHER -06

1022 LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATORv OI=CTHER INVESTIGATOR) PI - F.S. MOZER U OF CALIFORNIA, BERK BERKELEY, CA OI - M.C. KELLEY U OF CALIFCRNIA, BERK BERKELEY, CA 01 - C.G. FALTHAMMER RIT SWEDEN OI - K, KNOTT EUR SPACE TECH CENTER NCORDWIJKs THE NETHERLANDS 01 - A. PETERSEN EUR SPACE TECH CENTER NOORDWIJK, THE NETHERLANDS 01 - U.V. FAHLESC. ROYAL INST TECH STOCKHOLN SWEDEN

EXPERIMENT BRIEF DESCRIPTION THE OBJECTIVE OF THIS EXPERIMENT WILL BE TO STUDY THE QUASI-STATIC ELECTRIC FIELD IN THE PLASMASPHERE, MAGNETOSPHERE, MAGNETOSHEATH. AND SOLAR WIND. THE 4-IN.-DIAM SPHERES WILL BE MOUNTED AT THE END OF A 30-M BOOM IN THE SATELLITE SPIN PLANE. TO ATTEMPT TO OVERCOME THE SPACECRAFT SHEATH (A POTENTIAL PROBLEM WtICH PLAGUES MOST ELECTRIC FIELD DETECTORS), AN ELECTRON GUN IS INCLUDED ON THE SPACECRAFT BODY. THE INSTRUMENT IS TC BE SENSITIVE TO FIELDS FROM THRESHOLD TO 5 MV/M IN THE FREQUENCY BAND OF 0 TO 12 HZ.

****#***********t********************SEE-B ************

SPACECRAFT COMMON NAME- ISEE-B ALTERNATE NAMES- IMP-K PRIME, IME-D, DAUGHTER NSSDC ID- DAUGHTR

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 2-ALF 77 SPACECRAFT WEIGHT IN ORBIT- 120. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-CSS INTERNATIONAL ESRO

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 131000. KM ALT PERIAPSIS- 500. KM ALT INCLINATION- 28. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PRCJECT SCIENTIST) PM - A. HAWKYARO EUR SPACE TECH CENTER NOORDWIJK, THE NETHERLANDS PS - D.E. PAGE EUR SPACE TECH CENTER NCORDWIJK, THE NETHERLANDS

SPACECRAFT ORIEF DESCRIPTION THE EXPLORER CLASS DAUGHTER SPACECRAFT IS PART OF THE MOTHER/DAUGHTER/ELIOCENTRIC MISSION. THE PURPOSES OF THE MISSION WILL BE -- (1) TO INVESTIGATE SOLAR-TERRESTRIAL RELATIONSHIPS AT THE OUTERMOST BOUNDARIES OF THE EARTH'S MAGNETOSPHERE, (2) TO EXAMINE IN DETAIL THE STRUCTURE OF THE SOLAR WIND NEAR EARTH AND THE SHOCK WAVE THAT FORMS THE INTERFACE BETWEEN .THE SOLAR WIND AND EARTH, AND (3) TO CONTINUE THE INVESTIGATION CF COSMIC RAYS AND SOLAR FLARES IN THE INTERPLANETARY REGION NEAR I AU. THE MISSION WILL THUS EXTEND THE INVESTIGATIONS OF PREVIOUS IMP SPACECRAFT. THE MOTHER/DAUGHTER PORTION OF THE MISSION WILL CONSIST OF TWO SPACECRAFT WITH A STATION-KEEPING CAPABILITY IN A HIGHLY ECCENTRIC EARTH ORBIT WITH APOGEE FROM 18 TO 23 EARTH RADII. THE SPACECRAFT WILL MAINTAIN A SMALL SEPARATION DISTANCE, AND WILL MAKE SIMULTANEOUS COORDINATED MEASUREMENTS TO PERMIT SEPARATION OF SPATIAL FRCM TEMPORAL IRREGULARITIES IN THE NEAR-EARTH SOLAR WINDo THE BOW SHOCK, AND INSIDE THE NAGNETOSPHERE.

1023 ************ISEE-Be HARVEY

EXPERIMENT NAME- RACIO PROPAGATION RECEIVER NSSDC ID- DAUGHTR-06

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CT-ER INVESTIGATOR) PI - C.C. HARVEY PARIS OBSERVATORY MEUDONs FRANCE 01 - R. GENDRIN CNET PARIS, FRANCE 01 - J.R. MCAFEE NOAA BOULDER, CO 01 - M. PETIT CNET PARIS, FRANCE 01I - D. JONES EUR SPACE TECH CENTER NOORDWIJK, THE NETHERLANDS 01 - J.M. ETCHETO CNET PARIS. FRANCE 01 - R.J.L. GRARD EUR SPACE TECH CENTER NCORDWIJK, THE NETHERLANDS

EXPERIMENT BRIEF DESCRIPTION THE TOTAL ELECTRON CONTENT BETWEEN THE MOTHER AND DAUGHTER WILL BE OBTAINED BY MEASURING THE PHASE DELAY INTRODUCED EY THE AMBIENT PLASMA ONTO A WAVE OF FREQUENCY ABOUT 1 MHZ, TRANSMITTED FROM THE MOTHER (EXPERIMENT 8) AND RECEIVED ON THE DAUGHTER. THE PHASE WILL BE COMPARED AGAINST A PHASE-COHERENT SIGNAL TRANSMITTED FROM THE MOTHER TO THE DAUGHTER BY MODULATION ONTO A CARRIER OF FREQUENCY HIGH ENOUGH TC BE UNAFFECTED BY THE AMBIENT PLASMA.

SPACECRAFT COMMON NAME- IUE ALTERNATE NAMES- INT ULTRAVIOLET EXPL, SAS-D NSSDC ID- SAS-D

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 2HALF 76 SPACECRAFT WEIGHT IN CRBIT- 669. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS INTERNATIONAL ESRO SRC

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 1440. MIN APOAPSIS- 38000. KM ALT PERIAPSIS- 38000. KM ALT INCLINATION- 28.9 DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - G.W. LONGANECKER NASA-GSFC GREENBELT, MD PS - C.E. FICHTEL NASA-GSFC GREENBELT* MD PS - A. BOGGESS III NASA-GSFC GREENBELT, MD PS - A.B. UNDERHILL NASA-GSFC GREENBELT, MD

SPACECRAFT BRIEF DESCRIPTION THE INTERNATIONAL ULTRAVIOLET EXPLORER (IUE. FORMERLY SAS-D) SATELLITE IS AN APPROVED MISSION FOR THE CONSTRUCTION OF A SPACE-BORNE ULTRAVIOLET ASTRONOMICAL OBSERVATORY TO BE USED AS AANINTERNATICNAL FACILITY. THE IUE IS TO CONTAIN A 45-CM TELESCOPE USED SOLELY FOR SPECTROSCOPY IN THE WAVELENGTH RANGE OF 1100 TO 3300 A. THE PLANNING. CONSTRUCTION, AND ULTIMATE OPERATION

1024 OF THE IUE IS THE RESULT OF A CO-OPERATIVE INTERNATIONAL EFFORT. THE SATELLITE AND OPTICAL INSTRUMENTATION ARE TO BE PROVIDED BY THE GODDARD SPACE FLIGHT CENTER (GSFC). THE TELEVISION CAMERAS TO BE USED AS DETECTORS WILL BE PROVIDEC BY THE UNITED KINGDOM SPACE RESEARCH COUNCIL (UKSRC). THE EUROPEAN SPACE RESEARCH ORGANIZATION (ESRO) IS TO SUPPLY SOLAR PADDLES FOR THE SATELLITE AND WILL CONSTRUCT A EUROPEAN CONTROL CENTER. AFTER LAUNCH, TWO-THIRDS OF THE OBSERVING TIME WILL BE DIRECTED FROM A CONTROL CENTER AT GSFC, AND ONE-THIRD OF THE TIME THE SATELLITE.WILL BE OPERATED FROM THE EUROPEAN CONTROL CENTER NEAR MADRID. GUEST OBSERVERS WILL SUBMIT THEIR PROGRAMS FOR REVIEW AND EVALUATION TO EITHER NASA, UKSRC, OR ESRO AS THEY ARE RESIDENTS OF THE UNITED STATES, UNITED KINGDOM, OR ESRO CCUNTRIES. SCIENTISTS NOT COVERED BY THESE CONDITIONS WILL SUBMIT THEIR PROJECT PLANS TO ANY ONE OF THESE NATIONAL AGENCIES. TO ACHIEVE THE OBJECTIVE THAT THE IUE BE AN EFFECTIVE GUEST ASTRONOMICAL OBSERVATORY IT WILL BE LAUNCHED INTO A SYNCHRONOUS ORBIT. THE CHOICE OF A SYNCHRONOUS ORBIT IS MADE TO TRANSFORM THE PROBLEMS AND TECHNIQUES OF TELESCOPE OPERATION INTO A SEY SIMILAR TO THOSE FOR GROUND OBSERVATORIES, WHICH ARE ALREADY FAMILIAR TO EVERY OBSERVING ASTRONOMER. THE 45-CM RITCHEY-CHRETIEN F/15 TELESCOPE WILL FEED A SPECTROGRAPH PACKAGE. THE SPECTROGRAPH PACKAGE, USING SEC VIDICON CAMERAS AS DETECTORS WILL COVER THE SPECTRAL RANGE FROM 1100 TO 3300 A. IT WILL OPERATE IN EITHER A HIGH-RESOLUTION OR A LOW-RESOLUTION MODE, WITH RESOLUTIONS OF APPROXIMATELY 0.2 AND 6 A. RESPECTIVELY. THE SEC VIDICONS CAN INTEGRATE THE SIGNAL FOR UP TO I HR. THIS INTEGRATION TIME WILL LIMIT DETECTION IN THE HIGH- AND LOW-RESOLUTICN MODES TO APPROXIMATELY 5 AND 0.03 PHOTONS/(CM SO-SEC-ANGSTROM). RESPECTIVELY, FOR A SIGNAL-TO-NOISE RATIO OF 50. THESE SENSITIVITIES ARE EQUALIVALENT TO OBSERVATIONS OF A 80 STAR OF NINTH TO FOURTEENTH MAGNTUDE. RESPECTIVELY.

************IUE, NONE ASSIGNED

EXPERIMENT NAME- IUE LOW/HIGH RESOLUTION. ULTRAVIOLET SPECTROGRAPH PACKAGE NSSOC ID- SAS-D -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - NONE ASSIGNED

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL INCLUDE THE ULTRAVIOLET SPECTROGRAPH PACKAGE CARRIED BY THE IUE, CONSISTING OF TWO PHYSICALLY DISTINCT ECHELLE-SPECTROGRAPH/CAMERA UNITS CAPABLE OF ASTRCNCMICAL OBSERVATIONS. EACH SPECTROGRAPH WILL BE A THREE-ELEMENT ECHELLE SYSTEM, COMPOSED OF.AN OFF-AXIS PARABOLOIDAL COLLIMATOR, AN ECHELLE GRATING, AND A SPHERICAL FIRST-ORDER GRATING THAT WILL BE USED TO SEPARATE THE ECHELLE ORDERS AND, FOCUS THE SPECTRAL DISPLAY ON AN IMAGE CONVERTER-PLUS-SEC VIDICON CAMERA. (FOR EACH UNIT THERE WILL BE A SPARE CAMERA). THE CAMERA UNITS WILL BE ABLE TO INTEGRATE THE SIGNAL. THE READOUT/PREPARATION CYCLE FOR THE CAMERAS WILL TAKE APPROXIMATELY 4 MIN. WAVELENGTH CALIBRATION WILL EE PROVIDED BY THE USE OF A HOLLOW CATHODE COMPARISON LAMP. NO PHOTOMETRIC STANDARDS WILL BE CARRIED ON THE SPACECRAFT, BUT THE PHOTOMETRIC CALIBRATION WILL BE ACCOMPLISHED BY OBSERVING STANDARD STARS WHOSE SPECTRAL FLUXES HAVE BEEN PREVIOUSLY CALIBRATED BY OTHER MEANS. BOTH ECHELLE-SPECTROGRAPH/CAMERA UNITS WILL BE CAPABLE OF HIGH-RESOLUTION (0.2 A) OR LOW-RESOLUTION (6 A) PERFORMANCE. TFE DUAL HIGH/LOW RESOLUTION CAPABILITY WILL BE IMPLEMENTED EY THE INSERTION OF A FLAT IN FRONT OF THE ECHELLE GRATING, SO THAT THE ONLY DISPERSION WILL BE PROVIDED BY THE SPHERICAL GRATING. AS THE SEC VIDICONS CAN INTEGRATE TFE SIGNAL FOR UP TO 1 HR. DATA WITH A SIGNAL-TC-NOISE RATIO

1025 OF 50 CAN BE OBTAINED FOR A DO STAR OF THE INTH AND FOURTEENTH MAGNITUDE IN THE HIGH- AND LOW-RESOLUTION MODES, RESPECTIVELY. THE DISTINGUISHING CHARACTERISTICS OF THE UNITS WILL BE THEIR WAVELENGTH COVERAGE. ONE UNIT WILL COVER THE WAVELENGTH RANGE FROM 1192 TO 1924 A IN THE HIGH-RESOLUTION MODE, AND 1135 TO 2085 A IN THE LOw-RESCLUTICN MCDE. FCR THE OTHER UNIT, THE RANGES WILL BE FROM 1893 TO 3031 At AND 1800 TO 3255 A FOR THE HIGH- AND LOW-RESOLUTION MCDES, RESPECTIVELY. EACH UNIT WILL ALSO HAVE ITS OWN CHOICE OF ENTRANCE APERTURES EITHER FOR A 3-ARC-SEC HOLE OR A 10-X 20-ARC-SEC SLOT. THE 10-X 20-ARC-SEC SLOTS CAN BE BLOCKED BY A COMMON SHUTTER, BUT THE 3-ARC-SEC APERTURE WILL ALWAYS BE OPEN. AS A RESULT, TWO APERTURE CONFIGURATIONS ARE POSSIBLE -- (1) BOTH 3-ARC-SEC APERTURES OPEN AND BOTH 10-X 20-ARC-SEC SLOTS CLOSED, OR (2) ALL FOUR APERTURES OPEN. WITH THIS INSTRUMENTATION, THE OBSERVATIONAL CPTIONS OPEN TC AN OBSERVER WILL BE LONG-WAVELENGTH AND/OR SHORT-WAVELENGTH SPECTROGRAPHs HIGH OR LCW RESOLUTION, AND LARGE OR SMALL APERTURES. EXPOSURES MAY BE MADE WITH THE TWO SPECTROGRAPHS SIMULTANEOUSLY, BUT REMEMBERING THAT THE ENTRANCE APERTURES FOR EACH ARE DISTINCT AND SEPARATED ON THE SKY BY ABOUT 1 MIN OF ARC. AN ADDITICNAL RESTRICTION IS THAT DATA CAN EE READ OUT OF ONLY ONE CAMERA AT A TIME. HOWEVER, ONE CAMERA MAY BE EXPOSING WHILE ONE CAMERA IS BEING READ OUT. THE CHOICE OF HIGH OR LOW RESOLUTION CAN BE MADE INDEPENDENTLY FCR THE TWO SPECTROGRAPHS SO THAT THE OPERATIONAL MODES OF THE UNITS NEED NOT BE THE SAME.

****************** *********.**************** **LAGEOS ******&# * ****

SPACECRAFT COMMON NAME- LAGECS ALTERNATE NAMES- LASER GEODYNAMIC SAT. NSSDC ID- LAGEOS

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 1 OTR 76 SPACECRAFT WEIGHT IN CRBIT- 682. KG

LAUNCH SITE- VANDENBERG AFB. UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-CA

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 3700. KM ALT PERIAPSIS- 3700. KM ALT INCLINATION- 50. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - R. DILLER NASA HEADOUARTERS WASHINGTON, DC

SPACECRAFT BRIEF DESCRIPTION LAGEOS WILL BE A VERY DENSE (HIGH MASS/AREA RATIO) LASER RETROREFLECTOR SATELLITE WHICH WILL PROVIDE A PERMANENT REFERENCE POINT IN A VERY STABLE ORBIT FOR SUCH PRECISION EARTH-DYNAMICS MEASUREMENTS AS CRUSTAL MOTIONS, REGIONAL STRAINS, FAULT MOTIONS, POLAR MOTION AND EARTH-ROTATION VARIATIONS, SOLID EARTH TIDES. AND OTHER KINEMATIC AND DYNAMIC PARAMETERS ASSOCIATED WITH EARTHQUAKE ASSESSMENT AND ALLEVIATION. LAGEOS, IN CONJUNCTION WITH APPROPRIATE LASER TRACKING SYSTEMS. WILL PERMIT EXTREME-PRECISION RANGING MEASUREMENTS FOR BOTH GEOMETRIC MODE (MULTILATERATION) AND ORBITAL DYNAMIC MOCDE DETERMINATIONS OF POSITIONS OF POINTS ON THE EARTH. IT WILL BE THE FIRST SPACECRAFT DEDICATED EXCLUSIVELY TO HIGH-PRECISION LASER RANGING AND WILL PROVIDE THE FIRST OPPORTUNITY TO ACQUIRE LASER-RANGING DATA THAT IS NOT DEGRADED BY ERRORS ORIGINATING IN THE TARGET SATELLITE. THE HIGH-ACCURACY RANGE MEASUREMENTS FROM THIS PERMANENT

1026 ORBITING REFERENCE POINT WILL BE USED TO ACCCMPLISH MANY EXTREME-PRECISION EARTH-DYNAMICS MEASUREMENTS REQUIRED BY THE EARTHQUAKE HAZARD ASSESSMENT AND .ALLEVIATION OBJECTIVES OF THE EARTH AND OCEAN PHYSICS APPLICATIONS PROGRAM (EOPAP). THE PERFORMANCE IN ORBIT OF LAGEOS WILL EE LIMITED ONLY BY DEGRADATION OF THE RETROREFLECTCRS. SO MANY DECADES OF USEFUL LIFE CAN BE EXPECTED. THE HIGH MASS-TO-AREA RATIO AND THE PRECISE, STABLE (ATTITUDE-INDEPENDENT) GEOMETRY OF THE SPACECRAFT IN CONCERT WITH THE PROPOSED ORBIT WILL MAKE THIS SATELLITE THE MOST PRECISE POSITION REFERENCE AVAILABLE. BECAUSE IT WILL BE VISIBLE IN ALL PARTS OF THE WGRLD AND WILL HAVE AN EXTENDED OPERATION LIFE IN ORBITI LAGEOS CAN SERVE AS A FUNDAMENTAL GLOBAL STANDARD FOR DECADES.

****** *##**#******************* ****** ***** *44LST ********

SPACECRAFT COMMON NAME- LST ALTERNATE NAMES- LARGE SPACE TELESCOPE NSSOC ID- LST

LAST REPORTED STATE- A PROPOSED MISSION

PLANNED LAUNCH DATE- 00/00/80 SPACECRAFT WEIGHT IN ORBIT- 9525. KG

LAUNCH SITE- CAPE KENNEDY. UNITED STATES LAUNCH VEHICLE- SHUTTLE

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 6928. KM ALT PERIAPSIS- 6928. KM ALT INCLINATION- 28.5 DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PS - C.R. OvDELL NASA-MSFC HUNTSVILLE, AL

SPACECRAFT BRIEF DESCRIPTION THE PROPOSED LARGE SPACE TELESCOPE (LST) WILL BE A SPACE-BORNE, DIFFRACTION-LIMITED TELESCOPE WITH A PLANNED EFFECTIVE APERTURE OF APPROXIMATELY 3 M. THE INITIAL LAUNCH OF THE LST INTO EARTH ORBIT IS EXPECTED iN LATE 1980. THE SPACE SHUTTLE WILL BE USED FOR INITIAL LAUNCH, IN-ORBIT SERVICING, AND FOR RETURN OF THE LST TO THE GROUND FOR MAINTENANCE. THE ANTICIPATED MINIMUM OPERATIONAL LIFETIME. EXCLUDING DOWN TIME FOR PERIODIC MAINTENANCE AND UPDATING. IS 15 YRS. THE LST SYSTEM WILL SERVE AS A NATIONAL ASTRONOMICAL SPACE OBSERVATORY FACILITY. THE USE OF THE ONBOARD INSTRUMENTATION WILL BE OPEN TO SCIENTISTS OF ALL CCUNTRIES. THUS. ITS DESIGN WILL BE MOST FLEXIBLE TO ALLOW FOR THE REPLACEMENT OF SCIENTIFIC INSTRUMENTATION WHEN NECESSARY, TO INCORPORATE TECHNOLOGICAL ADVANCES. AND TO SATISFY CHANGES IN THE OBSERVATIONAL INTERESTS OF THE ASTRONOMICAL COMMUNITY. INSTRUMENTATION UPDATING, REPAIR, OR REPLACEMENT WILL BE ACCOMPLISHED BY EITHER RETURN.OF THE LST TO THE GROUND, OR BY UTILIZING SUITED ASTRONAUTS FOR IN-ORBIT WORK. PRESENT PHASE E DEFINITION STUDIES INDICATE A DESIRABLE. COMPLEMENT OF INSTRUMENTS AS FCLLOWS -- (1) A HIGH-RESOLUTION CAMERA TO COVER THE SPECTRAL RANGE FROM 120 TO 1100 NM. (2) A HIGH-RESOLUTION SPECTROGRAPH, OF RESOLUTION APPROXIMATELY 10 TO THE FIFTH, FOR THE 120-TO-310 NM REGION, (3) A FAINT OBJECT SPECTROGRAPH FOR WORK IN THE 90-TO-1100 NM REGION, (4) AN ASTROMETRIC PACKAGE FOR DOING WORK ON DOUBLE STARS, PROPER MOTIONS, PARALLAXES, ETC., AND (5) AN INFRARED PHOTOMETER AND/CR SPECTROMETER TO COVER THE WAVELENGTH INTERVAL FROM I TO 1000 MICRONS.

1027 *********************#**************LUNAR POLAR ORB-DAUGHTER***************

SPACECRAFT COMMON NAME- LUNAR POLAR ORB-DAUGHTER ALTERNATE NAMES- ALPO, AUTO.LUNAR POLAR ORBITER NSSDC ID-- LPO-D

LAST REPORTED STATE- A PROPOSED MISSION

PLANNED LAUNCH DATE- PROPSD79 SPACECRAFT WEIGHT IN CRBIT- 80. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- LTTAT-DLTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- SELENOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 6000. KM ALT PERIAPSIS- E000. KM ALT INCLINATION- 0. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. FS=PROJECT SCIENTIST) PM - J.T. SHEA NASA-GSFC GREENBELT, MD PS - J. PHILPOTTS NASA-GSFC GREENBELT. MD

SPACECRAFT BRIEF DESCRIPTION THIS SPACECRAFT WILL BE FOR A PROPOSED PROBE OF THE LUNAR ENVIRONMENT. IT IS CONCEIVED TO BE COMPOSED OF TWO SPACECRAFT IN A MOTHER-DAUGHTER RELATIONSHIP. THE MOTHER SHIP WILL CONTAIN THE SCIENTIFIC EXPERIMENTS, WHICH WILL INCLLDE X-RAY, GAMMA-RAY, MAGNETIC FIELD. AND GRAVITY-DETECTING SENSORS. IT IS PROPOSED THAT THE MOTHER SHIP HAVE A CIRCULAR NEAR-POLAR. NON-STABLE ORBIT WITH AN INCLINATION OF 8E DEG AT AN ALTITUDE OF 100 KM. THE DAUGHTER SPACECRAFT, WHICH WILL BE A RANGING AND COMMUNICATION STATION, WILL BE SENT INTO AN EQUATORIAL CIRCULAR CRBIT AT AN ALTITUDE OF 6000 TO 12000 KM. IN ORBIT THE PAYLOADS ANTICIPATED WILL BE APPROXIMATELY 230 KG (500 LBS) FOR TI-E MCTHER SHIP AND ABOUT 80 KG (175 LBS) FOR THE DAUGHTER SHIP. THE SCIENTIFIC PAYLOAD WILL BE CCNSTRAINED TO A DELTA VEHICLE. THE PROJECT IS IN T-E STUDY PHASE NOW. IT IS EXPECTED THAT AFO'S WILL BE SENT OUT AT THE BEGINNING OF FISCAL '75 (07/01/74).

~~********************$******# LUNAR POLAR ORB-MCTHER *##***Q4******

SPACECRAFT COMMON NAME- LUNAR POLAR ORB-MOTHER ALTERNATE NAMES- ALPO, AUTO.LUNAR POLAR ORBITER NSSDC ID- LPO-M

LAST REPORTED STATE- A PROPOSED MISSION

PLANNED LAUNCH DATE- PRCPSD79 SPACECRAFT WEIGHT IN CRBIT- 230. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- LTTAT-DLTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- SELENOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 100. KM ALT PERIAPSIS- 100. KM ALT INCLINATION- 85. DEG

1028 SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - J.T. SHEA NASA-GSFC GREENBELT, MD PS - J. PHILPOTTS NASA-GSFC GREENBELT, MD

SPACECRAFT BRIEF DESCRIPTION LUNAR ENVIRONMENT. THIS SPACECRAFT WILL BE FOR A PROPOSED PROBE OF THE IT IS CONCEIVED TO BE COMPOSED OF TWO SPACECRAFT IN A MOTHER-DAUGHTER EXPERIMENTS, RELATIONSHIP. THE MOTHER SHIP WILL CONTAIN THE SCIENTIFIC WHICH WILL INCLLDE X-RAY, GAMNA-RAY, MAGNETIC FIELD, AND GRAVITY-DETECTING NEAR-POLAR. SENSORS. IT IS PROPOSED THAT THE MOTHER SHIP HAVE A CIRCULAR OF 100 KM. NON-STABLE ORBIT WITH AN INCLINATION OF 85 DEG AT AN ALTITUDE STATION, THE DAUGHTER SPACECRAFT, WHICH WILL BE A RANGING AND COMMUNICATION OF 6000 TO WILL BE SENT INTO AN EQUATORIAL CIRCULAR CRBIT AT AN ALTITUDE APPROXIMATELY 230 KG 12000 KM. IN ORBIT THE PAYLOADS ANTICIPATED WILL BE FOR THE DAUGHTER (500 LBS) FOR THE MOTHER SHIP AND ABOUT 80 KG (175 LBS) VEHICLE. THE SHIP. THE SCIENTIFIC PAYLOAD WILL BE CCNSTRAINED TO A DELTA WILL BE SENT PROJECT IS IN THE STUDY PHASE NOW. IT IS EXPECTED THAT AFO'S OUT AT THE BEGINNING OF FISCAL '75 (07/01/74).

SPACECRAFT COMMON NAME- MARINER 10 MARINER VENUS/ME ALTERNATE NAMES- MARINER 73, PL-732A, MARINER-J VENUS/MERCURY. NSSDC ID- 73-085A

THE STANDARD LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT DATA ACQUISITION RATE SINCE 11/03/73.

504. KG LAUNCH DATE- 11/03/73 SPACECRAFT WEIGHT IN ORBIT-

LAUNCH VEHICLE- ATLAS-CENT LAUNCH SITE- CAPE KENNEDY, UNITED STATES

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

SCIENTIST) SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT PASADENA, CA PM - W.E. GIBERSON NASA-JPL WASHINGTON, DC PS - N.W. CUNNINGPAM NASA HEADGUAFTERS

SPACECRAFT BRIEF DESCRIPTION OF ONE THIS SPACECRAFT WAS THE FIRST ONE TO USE THE GRAVITATIONAL PULL ON NOVEMBER 3, PLANET (VENUS) TO REACH ANOTHER (MERCURY). IT WAS LAUNCHED ABOARD AN 1973. AT 0545 UT FROM THE KENNEDY SPACE CENTER, FLORIDA, SPACECRAFT STRUCTURE ATLAS/CENTAUR ROCKET. AND WEIGHED 503 KG IN ORBIT. THE ELECTRONICS COMPARTMENTS. WAS AN 18.15-KG. EIGHT-SIDED FRAMEWORK WITH EIGHT SOLAR PANELS, EACH IT MEASURED 1.39 M DIAGONALLY AND 0.457 M IN DEPTH. TWO SUPPORTING 5.1 SQUARE 2.7 M LONG AND C.97 M WIDE, WERE ATTACHED AT THE TOP, WITH TWO METERS OF SOLAR CELL AREA. THE ROCKET ENGINE WAS LIQUID-FUELED. ON THREE AXES. IT SETS OF REACTION JETS USED TO STABILIZE THE SPACECRAFT OF A HONEYCOMB-DISC CARRIED A LOW-GAIN OMNIDIRECTIONAL ANTENNA, COMPOSED 55 CM. FEEDS PARABOLIC REFLECTOR, 1.37 M IN DIAMETER. WITH FOCAL LENGTH FREQUENCIES. THE ENABLED THE SPACECRAFT TO TRANSMIT AT S-BAND AND X-BAND ON THE UPPER RING SPACECRAFT CARRIED A CANOPUS STAR TRACKER. LOCATED SUN SENSORS ON THE STRUCTURE OF THE OCTAGONAL SATELLITE, AND ACQUISITICN WAS INSULATED WITH TIPS OF THE SOLAR PANELS. THE INTERIOR OF THE SPACECRAFT WAS DEPLOYED MULTILAYER THERvAL BLANKETS AT TOP AND BOTTOM. A SUNSHADE SIDE. AFTER LAUNCH TO PROTECT THE SPACECRAFT CN THE SOLAR-GRIENTED SURFACE. AND INSTRUMENTS ABOARD THE SPACECRAFT MEASURED THE ATMOSPHERIC, INCLUDED PHYSICAL CHARACTERISTICS OF MERCURY AND VENUS. EXPERIMENTS

1029 TELEVISION PHOTCGRAPHY, AND MAGNETIC FIELD, PLASMA, INFRARED RADIOMETRY, ULTRAVIOLET SPECTROSCOPY, AND RADIO SCIENCE OETECTORS. AN EXPERIMENTAL X-BAND HIGH-FREQUENCY TRANSMITTER WAS FLGON FOR THE FIRST TIME ON THIS SPACECRAFT. MARINER 10 WAS PLACED IN A PARKING ORBIT AFTER LAUNCH FOR APPROXIMATELY 25 MINUTES. THEN PLACED IN CRBIT AROUND THE SUN EN ROUTE TO VENUS. THE ORBIT DIRECTION WAS OPPOSITE TO THE MOTION OF THE EARTH AROUND THE SUN. MID-CCURSE CORRECTIONS WERE MADE. THE SPACECRAFT PASSED VENUS ON FEBRUARY 5, 1974, AT A DISTANCE OF 5300 KV. IT CROSSED THE ORBIT OF MERCURY ON MARCH 29, 1974, AT A DISTANCE OF ABOUT 1000 KM FROM THE SURFACE. THE TV AND ULTRAVIOLET EXPERIMENTS WERE TURNED ON THE COMET KOHOUTEK WHILE THE SPACECRAFT WAS ON THE WAY TO VENUS. THE MARINER 10 PROJECT WAS MANAGED BY NASA-JPL, PASADENA. CALIFORNIA.

************MARINER 10, BRIDGE

EXPERIMENT NAME- MEASUREMENT OF PLASMA ENVIRONMENT NSSDC ID- 73-085A-03

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 11/03/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTER INVESTIGATOR) PI - H.S. BRIDGE MIT CAMBRIDGE, MA 01 - J.H. BINSACK MIT CAMBRIDGE, MA 01 - A.J. LAZARUS MIT CAMBRIDGE, MA OI - S. OLBERT MIT CAMBRIDGE, MA 01 - S.J. BAME LOS ALAMOS SCI LAB LOS ALAMOS, NM 01 - M.D. MONTGOMERY LOS ALAMOS SCI LAB LOS ALAMOS. NM 01 - A.J. HUNDHAUSEN LOS ALAMOS SCI LAB LOS ALAMOS. NM OI - J.R. ASBRIDCE LOS ALAMOS SCI LAB LOS ALAMOS, NM OI - KW. OGILVIE NASA-GSFC GREENBELT, MD OI - L.F. BURLAGA NASA-GSFC GREENBELT, MD OI - R.E. HARTLE NASA-GSFC GREENBELT* MD OI - C.W. SNYDER NASA-JPL PASADENA, CA 01 - G.Lo SISCOE U OF CALIFCRNIA, LA LOS ANGELES, CA

EXPERIMENT BRIEF DESCRIPTION A SET OF hEMISPHERICAL ANALYZER PLATES AND AN ELECTRON MULTIPLIER ALL MOUNTED ON A SCAN PLATFORM, WILL BE PROGRAMMED WITH A SEQUENCE OF ANALYZER PLATE VOLTAGES TO DETERMINE THE DIRECTICNAL CHARACTERISTICS AND THE ENERGY SPECTRUM FOR ELECTRONS FROM 4 TO 400 EV AND IONS FROM 80 EV TO 8 KEV IN THE SOLAR WIND BETWEEN 0.4 AND I AU DISTANCE FROM THE SUN.

************MARINER 10. BRCAOFOOT

EXPERIMENT NAME- EUV SPECTROSCOPY NSSDC ID- 73-085A-05

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 11/03/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - A.L. BROADFOCT KITT PEAK NATL OBS TUCSON. AZ OI - M*B. MCELROY HARVARD U CAMBRIDGE, MA 0I - M.J.S. BELTON KITT PEAK NATL OBS TUCSON, AZ

EXPERIMENT BRIEF DESCRIPTION TWO EUV GRATING SPECTROMETERS WILL BE USED (1) TO DETECT THE PRESENCE OF AN ATMOSPHERE ON MERCURY AND DETERMINE ITS STRUCTURE AND COMPOSITIONo (2)

1030 TO OBSERVE AND CETERMINE THE STRUCTURE AND COMPOSITION OF THE VENUSIAN BACKGROUND ATMOSPHERE, (3) TO MAP THE DIFFUSE GALACTIC AND INTERPLANETARY AT 584 AND RADIATION, AND (4) TO OBSERVE THE EARTH GEOCORONA, ESPECIALLY BY 1216 A. THE EXISTENCE OF AN ATMOSPHERE CN MERCURY WILL BE DETERMINED SOLAR USING ONE OF THE SPECTROMETERS TO OBSERVE THE ATMOSPHERE DURING A -- EACH OCCULTATION IN FOUR CHANNELS -- 475 A. 740 A. 810 A, AND 890 USED TO OBSERVE HAVING A 40-A BANDWIDTH. THE SECOND SPECTROMETER WILL BE SOURCES IN AIRGLOW EMISSIONS FROM THE EARTH. MERCURY, VENUS AND BACKGROUND A, 1216 A, NINE CHANNELS -- 304 A, 584 A. 744 A, 736 A. 867 TO 879 As 1048 OF THE 1304 A. 1657 A. FROM THESE DATA. THE MOST LIKELY CONSTITUENTS ATMOSPHERES OF MERCURY AND VENUS WILL BE DETERMINED.

************MARINER 10, CtASE, JR.

EXPERIMENT NAME- TWO-CHANNEL IR RACIOMETER NSSDC ID- 73-085A-06

STANDARD LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE DATA ACQUISITION RATE SINCE 11/03/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTFER INVESTIGATOR) PI - S.C. CHASE. JR. SANTA BARBARA RSCH CTR GOLETA. CA HI 01 - D. MORRISON UNIVERSITY OF HAWAII HONOLULU. OI - G. MUNCH CAL TECH PASADENA, CA DI - G. NEUGEBAUER CAL TECH PASADENA. CA 01 - J.M. SAARI BOEING SCI RSCH LABS SEATTLE, WA CA 01 - E.D. MINER NASA-JPL PASADENA,

EXPERIMENT BRIEF DESCRIPTION AN INFRAREC RADIOMETER HAVING TWO CHANNELS, 22 TO 39 MICRONS (80 DEG K TO TO 300 DEG K) AND 10 TO 17 MICRONS (200 DEG K TO 650 DEG K), WILL BE USED OBSERVE THE THERMAL EMISSION FROM VENUS AND MERCURY IN TWO BROAD SPECTRAL BANDS. THE IR TfERMAL EMISSION FROM THE SURFACE OF MERCURY BETWEEN LATE AFTERNOON AND EARLY MORNING (LOCAL TIME) AND DEVIATIONS FROM THE AVERAGE BE THERMAL BEHAVIOR OF THE SURFACE WILL BE MEASURED. MEASUREMENTS WILL ALSO MADE OF THE BRICHTNESS TEMPERATURES OF VENUSIAN CLOUD TOPS AND LIMB DARKENINGPHENOMENA.

***********MARINER 10, HOWARD

EXPERIMENT NAME- S- AND X-BAND RADIO PROPAGATION NSSDC ID- 73-085A-02

STANDARD LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE DATA ACQUISITION RATE SINCE 11/03/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) CA PI - H.T. HOWARD STANFORD U STANFORD, PASADENA, CA OI - G.S. LEVY NASA-JPL MA 01 - I.I. SHAPIRO MIT CAMBRIOGE. CA 01 - G. FJELDBC NASA-JPL PASADENA. CA OI - A.J. KLIORE NASA-JPL PASADENA, CA OI - J.D. ANDERSON NASA-JPL PASADENA*

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE THE ONBOARD S- AND X-BAND RADIO SUBSYSTEMS TO OBTAIN INFORMATION ON THE MERCURIAN AND VENUSIAN MASSES, GRAVITIES, HARMONICS, EPHEMERIDES, IONOSPHERES, ATMOSPHERES, RADII, AND SURFACE CHARACTERISTICS.

1031 ************MARINER 10, MURRAY

EXPERIMENT NAME- TELEVISION PHOTOGRAPHY NSSDC ID- 73-085A-01

LAST REPORTED STATE- LAUNCHED AND OPERATING * ,**** AT ZERO DATA ACQUISITION RATE .E 04/03/74.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INV' GATOR. OI=CTHER INVESTIGATOR) PI - B.C. MURRAY CAL & PASADENA, CA OI - M.J.S. BELTON I v ATL CBS TUCSON, AZ OI - G.P. KUIPER ZO NA TUCZON, AZ 01 - V.E. SUOMI ISCCOSIN MADISCN, WI 01 - N.J. TRASK, JR. 4OLOGICAL SURVEY MENLO PARK, CA 01 - D.E. GAULT SA--ARC MOFFETT FIELD, CA OI - B.W. HAPKE U OF PITTSBURGH PITTSBURG, PA 01 - M.E. DAVIES RAND CORP SANTA MCNICA, CA 01 - B.T. O'LEARY CORNELL U ITHACA. NY

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL TAKE TELEVISION-VIDEO PHOTOGRAPHY OF BOTH VENUS AND MERCURY. THE OBJECTIVES OF THE EXPERIMENT WILL BE - (1) TO MAP AND IDENTIFY THE MAJOR FHYSIOGRAPHIC PROVINCES OF MERCURY, (2) TO DETERMINE THE ORIENTATION OF THE SPIN AXIS OF MERCURY, (3) TO COMBINE ALL CF THE MERCURY DATA TO ESTABLISH A CARTOGRAPHIC COORDINATE SYSTEM, (4) TO INVESTIGATE THE TIME-DEPENDENT PROPERTIES OF THE VENUS ULTRAVIOLET *CLOUDS** AND (5) TO OBTAIN HIGH-RESOLUTION IMAGERY OF THE MAIN CLOUDS OF VENUS. THE INSTRUMENT WILL BE A GEC I 'VIDICON TUBE.* IT WILL HAVE A 42-SEC FRAMING RATE AND A 0.48- BY 0.37-DEG FIELD OF VIEW AND WILL USE TWO SPHERICAL TELESCOPE 150-MM OPTICS. IT IS PLANNED THAT APPROXIMATELY 8350 PICTURES, WITH A RESOLUTION OF 100 M, WILL BE OBTAINED.

************MARINER 10, NESS

EXPERIMENT NAME- FLUXGATE MAGNETOMETER NSSDC ID- 73-085A-04

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 11/03/73,

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - N.F. NESS NASA-GSFC GREENBELT. MD 01 - K.W. BEHANNON NASA-GSFC GREENBELT* MD OI - R.P. LEPPING NASA-GSFC GREENBELT, MD 01 - Y.C. WHANG CATHOLIC U WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO TRIAXIAL FLUXGATE MAGNETOMETERS DESIGNED TO MAKE VECTOR MEASUREMENTS OF THE MAGNETIC FIELD IN THE VICINITY OF MERCURY AND VENUS AND IN THE INTERPLANETARY MEDIUM. EACH SENSOR WILL HAVE DUAL OPERATING RANGES OF MINUS TO PLUS 16 GAMMAS AND 128 GAMMAS. BIAS OFFSET CAPABILITY WILL EXTEND THE OPERATING RANGE TO MINUS TO PLUS 4096 GAMMAS.

************MARINER 10, SIMPSON

EXPERIMENT NAME- ENERGETIC PARTICLES NSSDC ID- 73-085A-07

1032 LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 11/03/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - J.A. SIMPSON U OF CHICAGO CHICAGO, IL OI - J.E. LAMPORT U OF CHICAGO- CHICAGO. IL

EXPERIMENT BRIEF DESCRIPTION SPECIES OF THIS EXPERIMENT WILL MEASURE THE CHEMICAL AND ISOTOPIC SOLAR CHARGED PARTICLES BOMBARDING THE ATMOSPHERE AND SURFACE OF MERCURY. THE MEASUREMENTS WILL ALSO INCLUDE A SEARCH FOR TRAPPED HIGH-ENERGY ELECTRONS AND PROTONS IN THE POSSIBLE MAGNETOSPHERES OF MERCURY AND VENUS. PROTONS THE CHARGED PARTICLE TELESCOPE WILL BE SENSITIVE TO ELECTRONS AND WITH ENERGIES E.GT. 200 KEV AND E.GT. 600 KEV, RESPECTIVELY.

SPACECRAFT COMMON NAME- MARINER 77A ALTERNATE NAMES- MARINER JUPITER/SATURN A. OUTER PLANETS A NSSDC ID- MARN77A

LAST REPORTED STATE- AN APPROVED MISSION

70. KG PLANNED LAUNCH DATE- 2HALF 77 SPACECRAFT WEIGHT IN ORBIT-'

TITAN-CENT LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE-

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - H. SCHURMEIER NASA-JPL PASADENA, CA

SPACECRAFT BRIEF DESCRIPTION THE OVERALL OBJECTIVES OF THE TWO SPACECRAFT, MARINER 77A AND MARINER SYSTEMS 778, WILL BE TO CONDUCT EXPLORATORY INVESTIGATIONS OF THE PLANETARY TO SATURN. OF JUPITER AND SATURN AND OF THE INTERPLANETARY MEDIUM OUT TWO PRIMARY EMPHASIS WILL BE PLACED ON COMPARATIVE STUDIES OF THESE PLANETARY SYSTEMS BY OBTAINING (1) MEASUREMENTS OF THE ENVIRONMENT. OR MORE OF THE ATMOSPHERE, AND BODY CHARACTERISTICS OF THE PLANETS AND ONE OF SATURN. SATELLITES OF EACH PLANET, (2) STUDIES OF THE NATURE OF THE RINGS AT AND (3) EXPLORATION OF THE INTERPLANETARY (OR INTERSTELLAR) MEDIUM BE ATTAINED BY INCREASING DISTANCES FROM THE SUN. THESE OBJECTIVES WILL COHERENT S- AND USING A VARIETY OF INSTRUMENTS AND METHODS INCLUDING TV, A X-BAND RF RECEIVER, AN INFRARED INTERFEROMETER, ULTRAVIOLET SPECTROMETER, FLUXGATE MAGNETOMETERS, FARADAY CUPS, A PARTICLE ANALYZER* PARTICLE SWEEP FREQUENCY TELESCOPES, THE SISYPHUS METHOD PHOTOPOLARIMETER. AND A MONTH OF EACH RADIO RECEIVER. THE TWO SPACECRAFT WILL BE LAUNCHED WITHIN A OTHER.

************MARINER 77A BELAMONT

EXPERIMENT NAME- LYMAN ALPHA SPECTROPHOTOMETER NSSDC ID- MARN77A-12

LAST REPORTED STATE- PRELAUNCH

1033 EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATCR) PI - J.E. BLAMONT CNRS VERRIERES-LE-BUISSON. FRANCE 01 - J.L. BERTAUX CNES BRETIGNEY, FRANCE

EXPERIMENT BRIEF DESCRIPTION A HIGH-RESOLUTION TWO-CHANNEL PHCTOMULTIPLIER WILL BE MOUNTED ON THE SCAN PLATFORM AND WILL BE FLOWN TO PROVIDE MEASUREMENTS FOR SEVERAL STUDIES, INCLUDING THOSE DEALING WITH THE SOLAR WIND GALACTIC MEDIUM INTERACTION. AND WITH THE THERMCSPHERES OF JUPITER AND SATURN. THE RESONANCE LINES MEASURED WILL BE AT 1216 A AND 3090 A. WITH A SPECTRAL RANGE OF PLUS CR MINUS 2.5 A FOR THt HYDPOGEN EMISSION *AND WITH A SPECTRAL RANGE OF PLUS OR MINUS 40 A FOR THE OH OXHYORILL EMISSION. WHEN MEASURING IN THE HIGH SPECTRAL RESOLUTION MODE, I[E. AT 0.01 At THE FIELD OF VIEW WILL BE 1 DEG BY 2.5 DEG.

*********************** ******MARINER 77 **+*4**+ *****

SPACECRAFT COMMON NAME- MARINER 778 ALTERNATE NAMES- MARINER JUPITER/SATURN O. OUTER PLANETS B NSSDC 10- MARN77E

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 21ALF 77 SPACECRAFT WEIGHT IN CRBIT- 70. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- TITAN-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - H. SCHURMEIER NASA-JPL PASADENA, CA

SPACECRAFT BRIEF DESCRIPTION THE OVERALL OBJECTIVES OF THE TWO SPACECRAFT, MARINER 77A AND MARINES 778, WILL BE TO CONDUCT EXPLORATORY INVESTIGATIONS OF THE PLANETARY SYSTEMS, JUPITER AND SATURN, AND OF THE INTERPLANETARY MEDIUM OUT TO SATURN. PRIMARY EMPHASIS WILL EE PLACED ON COMPARATIVE STUDIES OF THESE TWO PLANETARY SYSTEMS BY OBTAINING (1) MEASUREMENTS OF THE ENVIRONMENT, ATMOSPHERE, AND BODY CHARACTERISTICS OF THE PLANETS AND ONE OR MORE OF THE SATELLITES OF EACH PLANET. (2) STUDIES OF THE NATURE OF THE RINGS OF SATURN, AND (3) EXPLORATION OF THE INTERPLANETARY (OR INTERSTELLAR) MEDIUM AT INCREASING DISTANCES FROM THE SUN. THESE OBJECTIVES WILL BE OBTAINED USING A VARIETY OF INSTRUMENTS AND METHODS INCLUDING TV, A COHERENT S- AND X-BAND RF RECEIVER. AN INFRARED INTERFEROMETER. AN ULTRAVIOLET SPECTROMETER. FLUXGATE MAGNETOMETERS, FARADAY CUPS. A PARTICLE ANALYZER, PARTICLE TELESCOPES. THE SISYPHUS METHOD PHOTOPOLARIMETER, AND A SWEEP FREQUENCY RADIO RECEIVER. THE TWO SPACECRAFT WILL BE LAUNCHED WITHIN A MONTH OF EACH OTHER.

************MARINER 778, BLAMONI

EXPERIMENT NAME- LYMAN ALPHA SPECTROPHOTOMETER NSSDC ID- MARN778-12

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - J.E. BLAMONT CNRS VERRIERES-LE-BUISSON. FRANCE OI - J.L. BERTAUX CNES BRETIGNEY, FRANCE

1034 EXPERIMENT BRIEF DESCRIPTION A HIGH-RESOLUTION TWO-CHANNEL PHOTOMULTIPLIER WILL BE MOUNTED ON THE SCAN PLATFORM AND WILL BE FLOWN TO PROVIDE MEASUREMENTS FOR SEVERAL STUDIES. INCLUDING THOSE DEALING WITH THE SOLAR WIND GALACTIC MEDIUM INTERACTION. AND WITH THE THERMOSPHERES OF JUPITER AND SATURN. THE RESONANCE LINES MEASURED WILL BE AT 1216 A AND 3090 A, WITH A SPECTRAL RANGE OF PLUS OR MINUS 2.5 A FOR THE HYDROGEN EMISSION, AND WITH A SPECTRAL RANGE OF PLUS OR MINUS 40 A FOR THE OH EMISSION. WHEN MEASURING IN THE HIGH SPECTRAL RESOLUTION MODE. I.E. AT 0.01 A. THE FIELD OF VIEW WILL BE 1 DEG BY 2.5 DEG.

**********************************************METEST ***********

SPACECRAFT COMMON KANE- METEOSAT ALTERNATE NAMES- METEOROLOGICAL SATELLITE NSSDC ID- METOSAT

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 4 QTR 76 SPACECRAFT WEIGHT IN ORBIT- KG

LAUNCH SITE- CAPE KENNEDY* UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY INTERNATIONAL ESRO

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 1440. MIN APOAPSIS- 36000. KM ALT PERIAPSIS- 36000. KM ALT INCLINATION- DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST)

SPACECRAFT BRIEF DESCRIPTION METEOSAT WILL BE A GEOSTATIONARY SPACECRAFT AND WILL SERVE AS PART OF ESRO'S (EUROPEAN SPACE RESEARCH OFFICE) CONTRIBUTION TO GARP (GLOBAL ATMOSPHERIC RESEARCH PROJECT). THE SPIN-STABILIZED SPACECRAFT WILL BE EQUIPPED WITH A VISUAL-INFRARED SENSOR TO PROVIDE NEAR-CONTINUOUS OBSERVATIONS OF VARIOUS WEATHER FEATURES. AS PART OF GARP, THE SATELLITE WILL HELP TO SUPPLY DATA REQUIRED FOR GLCBAL DATA SETS, TO BE USED IN IMPROVEMENT OF MACHINE WEATHER FORECASTS. IN GENERAL, THE SPACECRAFT DESIGN. INSTRUMENTATION, AND OPERATION WILL BE SIMILAR TO SMS/GOES.

*******#***********+***********4 *******N4- ***BUS-********

SPACECRAFT COMMON NAME- NIMBUS-C ALTERNATE NAMES- NSSDC ID- NIMBS-G

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- I QTR 77 SPACECRAFT WEIGHT IN CRBIT- KG

LAUNCH SITE- VANDENBERG AFBO UNITED STATES LAUNCH VEHICLE-

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OA

PLANNED ORBIT PARAMETERS

1035 ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 108. MIN APOAPSIS- 1100. KM ALT PERIAPSIS- 1100. KM ALT INCLINATION- 100. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - J. SARGENT NASA-GSFC GREENBELT. MD PS - W.R. BANDEEN NASA-GSFC GREENeELT, MD

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kUS WILL PROVIDE MOUNTING SPACE FOR SENSORS AND ANTENNAS. A BOX-BEAM STRUCTURE MOUNTED WITHIN THE CENTER OF THE TORUS WILL PROVIDE SUPPORT FOR THE LARGER SENSOR EXPERIMENTS. MOUNTED ON THE CONTROL HOUSING UNIT, WHICH WILL BE LOCATED ON TOP OF THE SPACECRAFT. WILL BE SUN SENSORS, HORIZON SCANNERS, AND A COMMAND ANTENNA. AN ADVANCED ATTITUDE CONTROL SYSTEM WILL PERMIT THE SPACECRAFT'S ORIENTATION TO BE CONTROLLED TO WITHIN PLUS OR MINUS 1 DEG IN ALL THREE AXES (PITCH, ROLL, AND YAW). NINE EXPERIMENTS HAVE BEEN SELECTED. THEY ARE (1) LACATE - LOWER ATMOSPHERIC COMPOSITION AND TEMPERATURE* (2) SANS - STRATOSPHERIC AND MESOSPHERIC SOUNDER, (3) CZCS - COASTAL ZONE OCEAN COLOR SCANNER, (4) THIR - TEMPERATURE AND HUMIDITY INFRARED RADIOMETER, (5) MAPS - MEASUREMENT OF AIR POLLUTION FRCM SATELLITEs (6) SAM - STRATOSPHERIC AEROSOL MEASUREMENTt (7) ERE - EARTH RADIATION BUDGET* (8) SMMR - SCANNING MICROWAVE RADIOMETER, AND (9) BUV/TOMS - UACKSCATTER UV/TOTAL OZONE MAPPING STUDY. THIS COMPLEMENT CF SENSORS WILL BE CAPABLE OF DEOSERVING SEVERAL PARAMETERS OF IMPORTANCE AT AND BELOW THE MESOSPHERIC LEVELS. A NEW CAPABILITY CF IMPORTANCE WILL BE DIRECTED TOWARD OBSERVATION OF ATMOSPHERIC AND OCEAN PCLLUTANTS. SUFFICIENT RUNTIME IS PLANNED FOR SEQUENTIAL MAPS (IMAGERY) OF THE PARAMETERS TO BE AVAILABLE FOR STUDY.

**************************** ***********PIONEER 10 ****+

SPACECRAFT COMMON NAME- PIONEER 10 ALTERNATE NAMES- PIONEER-F, PL-723D, 0560 NSSOC ID- 72-012A

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 03/03/72.

LAUNCH DATE- 03/03/72 SPACECRAFT WEIGHT IN ORBIT- 231. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- ATLAS-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - C.F. HALL NASA-ARC MOFFETT FIELDO CA PS - J.H. WOLFE NASA-ARC MOFFETT FIELD, CA

1036 SPACECRAFT BRIEF DESCRIPTION PIONEER 1C WAS THE FIRST OF TWO 258-KG. SPIN-STABILIZED (AT 4.8 RPM)* EARTH-POINTING SPACECRAFT DESIGNED TO PROVIDE INFORMATION ON THE INTERPLANETARY MEDIUM, THE ASTEROID BELT. AND JUPITER AND ITS ENVIRONMENT. THE SPACECRAFT COMPLEMENT OF 11 EXPERIMENTS INCLUDED PLASMA AND ENERGETIC PARTICLE DETECTORS, A MAGNETOMETER, METEROID DETECTORS, AN IMAGING PHOTOPULARIMETER. A UV PHOTOMETER AND AN IR RADIOMETER. PASSIVE IONOSPHERIC OCCULTATION AND CELESTIAL MECHANICS STUDIES WERE ALSO CARRIED OUT. POWER WAS PROVIDED BY FOUR BOOM-MOUNTED RADICISOTOPE THERMOELECTRIC GENERATORS. EIGHT BIT RATES (8 TO 2048 EPS) WERE AVAILABLE. DURING JOVIAN ENCOUNTER THE BIT RATE WAS 1024 BPS. PIONEER 10 CROSSED THE JOVIAN BOW SHOCK AT ABOUT 108 PLANETARY RADII CN NOVEMBER 26, 1973. ALMOST 21 MONTHS AFTER LAUNCH, AND AFTER SURVIVING ITS TRANSIT OF THE ASTEROID BELT WITH NO DAMAGE. CLOSEST APPROACH OCCURRED ON CECEMBER 4, 1973, AT 130,000 KM (1.8 PLANETARY RADII) ABOVE THE CLOUD TOPS. FINAL EXIT FROM THE JOVIAN MAGNETOSHEATH OCCURRED AT ABOUT 240 PLANETARY RADII. DESPITE THE INTENSE FLUXES OF VERY ENERGETIC PARTICLES, THE SPACECRAFT SYSTEMS (EXCEPT THE SPACECRAFT STELLAR REFERENCE ASSEMBLY) AND EXPERIMENTS (EXCEPT FOR THE ASTEROID-METEOROID DETECTOR) SURVIVED THE JOVIAN ENCOUNTER WELL. THE SPACECRAFT IS NOW ON A TRAJECTORY OF ESCAPE FROM THE SOLAR SYSTEM. IT IS EXPECTED.TO TRANSMIT DATA UNTIL 1977, WHEN THE SPACECRAFT WILL BE ABOUT 20 AU DISTANT.

************PIChEER 10, GEHRELS

EXPERIMENT NAME- IMAGING PHOTOPCLARIMETER (IPP) NSSOC ID- 72-012A-07

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 03/03/72.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - T. GEHRELS U OF ARIZONA TUCSON. AZ OI - D.L. COFFEEN U OF ARIZONA TUCSON. AZ UI - J. HAMEEN-ANTILLA U OF ARIZONA TUCSON. AZ OI - C.E. KENKNIGHT U OF ARIZONA TUCSON, AZ 0I - R.F. HUMMER SANTA BARBARA RSCH CEN GOLETA, CA OI - M.G. TOMASKO U OF ARIZONA TUCZON. AZ

EXPERIMENT BRIEF DESCRIPTION THE IMAGING PHOTOPOLARIMETER EXPERIMENT (IPP) WAS USED DURING JOVIAN ENCOUNTER TO MAKE SIMULTANEOUS TWO-COLOR (BLUE - 3900 TO 4900 A. RED - 5800 TO 7000 A) POLAPIMETRIC AND RADIOMETRIC MEASUREMENTS, AND MODERATE-RESOLUTION (ABOUT 200 KM AT BEST) SPIN-SCAN IMAGES OF JUPITER AND THE JOVIAN SATELLITES. THE POLARIMETRIC AND RADICMETRIC WORK WAS PERFORMED USING AN 8- X 8- MRAD FIELD-STOP APERTURE, WHILE THE SPIN-SCAN IMAGING USEC A 0.5- X 0.5-MRAD APERTURE STOP. RELATIVE RADICMETRIC CALIBRATION WAS DERIVED USING AN INTERNAL TUNGSTEN LAMP. LONG-TERM ABSOLUTE CALIBRATION OF THE INSTRUMENT WAS ACCOMPLISHED BY MEANS OF A SUNLIGHT DIFFUSOR/ATTENUATOR ELEMENT LOCATED IN THE SPACECRAFT ANTENNA STRUCTURE, I.E., PRIMARY RADIOMETRIC CALIBRATION WAS OBTAINED THROUGHOUT THE MISSION BY PERIODICALLY COMMANDING THE TELESCOPE TO VIEW THIS DIFFUSE-BACKLIGHTED (SUNLIGHT) SOURCE. THE EXPERIMENTAL TRAIN FOR THE IPP,PACKAGE CONSISTED OF THE FOLLOWING ELEMENTS -- (1) A NEAR-DIFFRACTION-LIMITED 2.54-CM MAKSUTOV CATADIOPTRIC TELESCOPE (F/3.4), (2) A FOCAL PLANE WHEEL CONTAINING FIELD-OF-VIEW APERTURES. DEPOLARIZERS, CALIBRATION SOURCE, ETC., (3) A WOLLASTON PRISM TC SPLIT LIGHT INTO TWO ORTHOGONALLY POLARIZED BEAMS, (4) A 45-DEG DICHROMATIC MIRROR THAT REFLECTED WAVELENGTHS LESS THAN 5500 A (BLUE BEAM) AND TRANSMITTED ALL LIGF-T OF GREATER WAVELENGTH (RED BEAMi) (5) FOR EACH SPECTRAL BEAM (TWO POLARIZATIONS), A FILTERING COATED RELAY LENS AND FOLDING

1037 MIRRORS, AND (6) FOR EACH SPECTRAL BEAM, TWO BENDIX CHANNELTRON DETECTORS (BLUE BIALKALI S-11 PHOTOCATHODES RED S-20 PHOTOCATHODES) TO REGISTER THE INTENSITY IN EACF POLARIZATION COMPONENT. (NOTE - THIS EXPERIMENT WAS ALSC ABOARD PIONEER 11).

************PIONEER 10, WEINBERG

EXPERIMENT NAME- ZODIACAL-LIGHT TWO-COLOR PHCTOPCLARIMETRY NSSDC ID- 72-312A-14

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNCWN DATA ACQUISITION RATE SINCE 02/27/74.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - J.L. WEINBERG STATE U OF NEW YORK ALBANY, NY OI - M.S. HANNER STATE U OF NEW YORK ALBANY, NY

EXPERIMENT BRIEF DESCRIFTION THE IMAGING PHOTOPOLARIMETER EXPERIMENT (IPP) WAS USED TO OBTAIN MAPS OF THE ZODICAL LIGHT DISTRIBUTION IN TWC COLORS. BLUE (3900 TO 4900 A) AND RED (5800 TO 7000 A). IN EACH COLOR. THE MAPS WERE CONSTRUCTED OUT OF THE INTEGRATED-DETECTOR-RESPONSE (1/64 OF A ROLL PERICOD), SPIN-SCAN POINT-IMAGING DATA OBTAINED BY VIEWING THROUGH A 40- X 40-MRAD SO FIELD-STOP APERTURE. THIS WORK WAS PERFORMED DURING THE CRUISE PORTION OF THE MISSION. DETAILED SIMULTANEOUS RADIOMETRIC AND PCLARIMETRIC MAPS OF BOTH SKY COLORS WERE MADE AS ThE SPACECRAFT SWEPT OUT A 360-DEG CLOCK ANGLE SWATH* AND THE TELESCOPE AND OPTICS WERE STEPPED IN CONE ANGLE (THE ANGLE BETWEEN SPACECRAFT SPIN AXIS AND THE TELESCOPE OPTICAL AXIS). AT EACH DISCRETE CONE ANGLE, A 20 ROLL MEASUREMENT CYCLE OCCURRED, CONSISTING OF 10 ROLLS FOR THE ACCUMULATION OF THE DATA AND FOR CALIOBRATION, ALTERNATED WITH 10 ROLL PERIODS USED FOR THE TELEMETRY OF THE DATA. DURING A DATA ROLL. THE SIGNALS FROM FOUR DETECTORS (2/COLOR) WERE INTEGRATED OVER A TIME INTERVAL EQUAL TC 1/64 OF THE ROLL PERIOD. THE FOUR CHANNELS PROVIDED SIMULTANEOUS MEASUREMENTS AT TWO ORTHOGONAL POLARIZATION AZIMUTHS IN THE TWO SPECTRAL BANDS. THE POLARIZATION WAS SAMPLED PARALLEL AND PERPENDICULAR TO THE PLANE CONTAINING THE SPACECRAFT SPIN AXIS AND THE OPTICAL AXIS OF THE TELESCOPE. RADIOACTIVE CALIBRATION WAS PROVIDED BY A RADIOISOTOPE-ACTIVATED PHOSPHOR SOURCE. ALL SUCH DATA WERE FORMATTED TO PRODUCE A SKY MAP, 360 DEG IN CLOCK ANGLE BY 141 DEG IN CONE ANGLE. THE EXPERIMENTAL TRAIN FOR THE IPP PACKAGE CONSISTED OF THE FOLLOWING ELEMENTS -- (1) A NEAR-DIFFRACTION-LIMITED 2.54-CM MAKSUTOV CATADIOPTRIC TELESCOPE (F/3.4)v (2) A FOCAL PLANE WHEEL CONTAINING FIELD-OF-VIEW APERTURES, DEPOLARIZERS, CALIBRATION SOURCE. ETC.. (3) A WOLLASTON PRISM TO SPLIT LIGHT INTO TWO ORTHOGONALLY POLARIZED BEAMS, (4) A 45-DEG DICFROMATIC MIRROR THAT REFLECTED WAVELENGTHS LESS THAN 5500 A (BLUE BEAM) AND TRANSMITTED ALL LIGHT OF GREATER WAVELENGTH (RED BEAM). (5) FOR EACH SPECTRAL BEAM (TWO POLARIZATIONS). A FILTERING COATED RELAY LENS AND FOLDING MIRRORS, AND (6) FOR EACH SPECTRAL BEAM. TWO BENDIX CHANNELTRON DETECTORS (BLUE - BIALKALI S-11 PHOTOCATHODES. RED-S-20 PHOTOCATHODES) TO REGISTER THE INTENSITY IN EACH POLARIZATION COMPONENT. (NOTE - THIS EXPERIMENT WAS ALSO ABOARD PIONEER 11).

***************4************************PION*E* 11 **********

SPACECRAFT COMMON NAME- PIONEER 11 ALTERNATE NAMES- PIONEER-G, PL-733C 6421 NSSDC ID- 73-019A

1038 LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 04/06/73.

LAUNCH DATE- 04/06/73 SPACECRAFT WEIGHT IN GRBIT- 231. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- ATLAS-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-CSS

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - C.F. HALL NASA-ARC MOFFETT FIELD, CA PS - J.H. WOLFE NASA-ARC MOFFETT FIELD, CA

SPACECRAFT BRIEF DESCRIPTION PIONEER 11 WAS THE SECOND OF TWO 231-KG, SPIN-STABILIZED EARTH POINTING SPACECRAFT DESIGNED TO PROVIDE INFORMATION ON THE INTERPLANETARY MEDIUM, THE ASTEROID BELT AND THE NEAR-JUPITER ENVIRONMENT. THIS JUPITER FLY-BY SPACECRAFT WAS POWERED BY A RADIOISOTOPE THERMOELECTRIC GENERATOR AND A BATTERY. THE SPACECRAFT INSTRUMENTATION STUDIED THE INTERPLANETARY AND POSSIBLE JOVIAN MAGNETIC FIELDS, THE SOLAR WIND AND POSSIBLE JOVIAN BOW SHOCK AND MAGNETOPAUSE BOUNDARIES, SOLAR AND GALACTIC COSMIC RAYS, INTERPLANETARY CHARGED PARTICLES AND POSSIBLE JOVIAN TRAPPED RADIATION. JOVIAN THERMAL ENERGY FLUX, ZODIACAL LIGHT, ASTEROIDS AND METEOROIDS, AND INTERPLANETARY AND JOVIAN ULTRAVIOLET RADIATION. AN S-BAND OCCULTATION EXPERIMENT AND A JUPITER IMAGING AND PHOTOPOLARIZATION EXPERIMENT WERE PERFORMED. THE SPACECRAFT WAS TO GO BY JUPITER BETWEEN 600 AND 750 DAYS AFTER LAUNCH ANC , DEPENDING ON THE AMOUNT OF THRUSTER FUEL LEFT AFTER THE JUPITER ENCOUNTER, CONTINUE ON TO ENCOUNTER WITH SATURN APPROXIMATELY 7 YEARS AFTER LAUNCH.

************PIONEER 11, GEHRELS

EXPERIMENT NAME- IMAGING PHOTOPOLARIMETER NSSDC ID- 73-019A-07

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT THE STANDARD DATA ACQUISITION RATE SINCE 04/06/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OThER INVESTIGATOR) PI - T. GEHRELS U OF ARIZONA TUCSON, AZ OI - D.L. COFFEEN U OF ARIZONA TUCSON, AZ 01 - J. HAMEEN-ANTILLA U OF ARIZONA TUCSON, AZ 01 - C.E. KENKNIGHT U OF ARIZONA TUCSON, AZ 01 - R.F. HUMMER SANTA BARBARA RSCH CEN GOLETA, CA 01 - M.G. TOMASKO U OF ARIZONA TUCZON, AZ

EXPERIMENT BRIEF DESCRIPTION THE IMAGING PHOTOPOLARIMETER EXPERIMENT (IPP) WAS USED DURING JOVIAN ENCOUNTER TO MAKE SIMULTANEOUS, TWO COLOR (BLUE - 3900 TO 4900 A, RED - 5800 TO 7000 A) POLARIMETRIC AND RADIOMETRIC MEASUREMENTS. AND MODERATE RESOLUTION (ABOUT 2C0 KM AT BEST) SPIN-SCAN IMAGES CF JUPITER AND THE JOVIAN SATELLITES. THE POLARIMETRIC AND RADIOMETRIC WORK WAS PERFORMED USING AN 8- X 8-MRAD FIELD-STOP APERTURE, WHILE THE SPIN-SCAN IMAGING USED A 0.5- X 3.5-MRAD APERTURE STOP. RELATIVE RADICMETRIC CALIBRATION WAS DERIVED USING AN INTERNAL TUNGSTEN LAMP. LONG-TERM ABSOLUTE CALIBRATION OF THE INSTRUMENT WAS ACCOMPLISHED BY MEANS OF A SUNLIGHT DIFFUSOR/ATTENUATOR ELEMENT LOCATEC IN THE SPACECRAFT ANTENNA STRUCTURE. TFAT IS, PRIMARY RADICMETRIC CALIBRATION WAS OBTAINED THROUGHOUT THE MISSION BY PERIODICALLY COMMANDING

103S THE TELESCOPE TO VIEW THIS DIFFUSE BACKLIGHTED (SLNLIGHT) SOURCE. THE EXPERIMENTAL TRAIN FOR THE IPP PACKAGE CONSISTED OF THE FOLLOWING ELEMENTS -- (1) A NEAR-DIFFRACTION-LIMITED 2.54-CM MATSUTOL TELESCCPE OF FOCAL RATIC F/3.4, (2) A FOCAL PLANE WHEEL CONTAINING FOV APERTURES, DEPOLARIZERS, CALIBRATION SOURCE, ETC., (3) A WOLLASTCN PRISM TO SPLIT THE LIGHT INTO TWC ORTHOGONALLY POLARIZED BEAMS, (4) A 45-DEG DICHROMATIC MIRROR THAT REFLECTS WAVELENGTHS OF LESS THAN 5500 A (BLUE BEAN) AND TRANSMITS ALL L'IGHT OF GREATER WAVELENGTH (RED BEAM), (5) FOR EACH SPECTRAL BEAM (TWO POLARIZATIONS ARE SEPARATED) A FILTERING-COATED RELAY LENS, AND FOLDING MIRRORS, AND (6) FINALLY, FOR EACH SPECTRAL BEAM TWO BENDIX CHANNELTRON (BLUE - BIALKALI S-11 PHOTOCATHODES, RED - S-20 PHOTOCATHODES) TO REGISTER THE INTENSITY IN EACH POLARIZATION CCMFONENT. (NOTE - THIS EXPERIMENT WAS ALSO ABOARD PIONEER 10.)

************PIONEER 11. WEINBERG

EXPERIMENT NAME- ZODIACAL-LIGHT TWO-COLOR PHOTOPOLARIMETRY NSSDC ID- 73-019A-15

LAST REPORTED STATE- LAUNCHED AND OPERATING NORMALLY AT AN UNKNCWN DATA ACQUISITION RATE SINCE 02/27/74.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - J.L. WEINBERG STATE U OF NEW YORK ALBANY, NY I0 - M.S. HANNER STATE U OF NEW YORK ALBANY, NY

EXPERIMENT BRIEF DESCRIPTION THE IMAGING PHOTOPOLARIMETER EXPERIMENT (IPP) WAS USED TO OBTAIN MAPS OF THE ZODIACAL LIGHT DISTRIBUTION IN TWO COLORS, BLUE (3900 TO 4900 A) AND RED (5800 TO 7000 A). IN EACH .COLOR. THE MAPS WERE CONSTRUCTED OUT OF THE INTEGRATED-DETECTOR-RESPONSE (1/64 OF A ROLL PERIOD)* SPIN-SCAN POINT-IMAGING DATA OBTAINED BY VIEWING THROUGH A 40- X 40-MRAD SQ FIELD-STOP APERTURE. THIS WORK WAS PERFORMED DURING THE CRUISE PORTION OF THE MISSION. IN DETAIL, SIMULTANEOUS RADIOMETRIC AND POLARIMETRIC MAPS OF THE SKY IN BOTH COLORS WERE MADE AS THE SPACECRAFT SWEEPED OUT A 360-DEG CLOCK ANGLE SWATH. AND THE TELESCOPE AND OPTICS WERE STEPPED IN CONE ANGLE (THE ANGLE BETWEEN SPACECRAFT SPIN AXIS AND THE TELESCOPE OPTICAL AXIS). AT EACH DISCRETE CONE ANGLE, A 20 RCLL MEASUREMENT CYCLE OCCURRED, CONSISTING OF 10 ROLLS FOR THE ACCUMULATION OF THE DATA AND FOR CALIBRATION, ALTERNATED WITH 10 ROLL PERIODS USED FOR THE TELEMETRY CF THE DATA. DURING A DATA ROLL. THE SIGNALS FROM FOUR DETECTORS (2/COLOR) WERE INTEGRATED OVER A TIME INTERVAL EQUAL TO 1/64 OF THE ROLL PERIOD. THE FOUR CHANNELS PROVIDED SIMULTANEOUS MEASUREMENTS AT TWO ORTHOGONAL POLARIZATION AZIMUTHS IN THE TWO SPECTRAL BANDS. THE POLARIZANCE WAS SAMPLED PARALLEL AND PERPENDICULAR TO THE PLANE CONTAINING THE SPACECRAFT SPIN AXIS AND THE OPTICAL AXIS OF THE TELESCOPE. RADIOACTIVE CALIBRATION WAS PROVIDED BY A RADIOISOTOPE-ACTIVATED PHOSPHOR SOURCE. ALL SUCH DATA WERE FORMATTED TO PRODUCE A SKY MAP, 360 DEG IN CLOCK ANGLE BY 141 DEG IN CONE ANGLE. THE EXPERIMENTAL TRAIN FOR THE IPP PACKAGE CONSISTED OF THE FOLLOWING ELEMENTS -- (1) A NEAR-DIFFRACTION-LIMITED 2.54-CM MAKSUTOV CATADIOPTRIC TELESCOPE (F/3.4), (2) A FOCAL PLANE WHEEL CONTAINING FIELC-OF-VIEW APERTURES, DEPOLARIZERS, CALIBRATION SOURCE, ETC., (3) A WOLLASTON PRISM TO SPLIT THE LIGHT INTO TWO ORTHOGONALLY POLARIZED BEAMS. (4) A 45-DEG DICHROMATIC MIRROR THAT REFLECTED WAVELENGTHS LESS THAN 5500 A (BLUE BEAM) AND TRANSMITTED ALL LIGHT OF GREATER WAVELENGTH (RED BEAM), (5) FOR EACH SPECTRAL BEAM (TWO POLARIZATICNS) A FILTERING-COATED RELAY LENS. AND FOLDING MIRRORS9 AND (6) FOR EACH SPECTRAL BEAMs TWO BENDIX CHANNELTRON DETECTORS (BLUE - BIALKALI S-11 PHOTOCATHODES, RED - S-20 PHOTOCATHODES) TO REGISTER THE INTENSITY IN EACH POLARIZATICN COMPONENT.

1040 (NOTE THIS EXPERIMENT WAS ALSO ABOARD PIONEER 10).

*********4#*#*lt*** ***********************RM 20 ************

SPACECRAFT COMMON NAME- RM 20 ALTERNATE NAMES- SESP P72-2A, ST 72-2A NSSDC ID- RM20

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 11/01/74 SPACECRAFT WEIGHT IN ORBIT- 204. KG

F LAUNCH SITE- VANDENBERG AFB, UNITED STATES LAUNCH VEHICLE- ATLAS

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-U.SAF

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN 90. DEG APOAPSIS- 750. KM ALT PERIAPSIS- 750. KM ALT INCLINATION-

SPACECRAFT PERSONNEL (PM=PRCJECT MANAGER. PS=PROJECT SCIENTIST)

SPACECRAFT BRIEF DESCRIPTION THIS SATELLITE WILL BE A LOW-ALTITUDE SATELLITE IN CIRCULAR ORBIT FROM CARRYING FOUR EXPERIMENTS. TWO OF THE EXPERIMENTS WILL STUDY RADIATION THE EARTH HORIZON. A THIRD EXPERIMENT WILL OBSERVE SOLAR EXTINCTION THROUGH THE STRATOSPHERE ANC THE FOURTH WILL STUDY IONOSPHERIC RADIO PROPAGATION. THE SPACECRAFT EXPERIMENT SUPPORT EQUIPMENT WILL INCLUDE A 3-AXIS STABILIZATION SYSTEM AND A TAPE RECORDER.

+3################*##+##*####*SS 74-2 **************

SPACECRAFT COMMON NAME- SESP 74-2 ALTERNATE NAMES- S3-3 NSSDC ID- ST74-2A

LAST REPORTED STATE- AN APPROVED MISSION

KG PLANNED LAUNCH DATE- 08/00/75 SPACECRAFT WEIGHT IN CRBIT-

LAUNCH SITE- VANDENBERG AFB, UNITED STATES LAUNCH VEHICLE-

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-USAF

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN DEG APOAPSIS- 8000. KM ALT PERIAPSIS- 200. KM ALT INCLINATION-

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - UNKNOWN UNKNOWN PS - UNKNOWN UNKNOWN

SPACECRAFT BRIEF DESCRIPTION THIS SPACECRAFT WILL BE A SMALL OBSERVATORY WITH EIGHT DIFFERENT PARAMETERS AND SENSORS ON BOARC, DESIGNED TO OBSERVE VARIOUS MAGNETOSPHERIC AND ALPHA THEIR INTERRELATIONSHIPS. SENSORS OBSERVING ENERGETIC PROTONS THE SPACE PARTICLES WILL ALSO PROVIDE REAL-TIME OBSERVATIONS FOR USE BY

1041 FORECAST FACILITY (USAF-AWS). INFORMATICON OF THE SPACECRAFT SIZE, SHAPE, POWER SYSTEM, ALTITUDE SYSTEM, ETC. ARE NOT YET AVAILABLE. THIS IS THE THIRD SPACECRAFT OF A NEW DESIGN WHICH HAS BEEN DEVELOPED FOR DOD USE.

*******************************************SESP P73-S #######e##ttee

SPACECRAFT COMMON NAME- SESP P73-5 ALTERNATE NAMES- 53-1 NSSOC ID- ST73-5A

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 08/00/74 SPACECRAFT WEIGHT IN CRBIT- KG

LAUNCH SITE- VANDENBERG AFB. UNITED STATES LAUNCH VEHICLE-

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-USAF

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- MIN APOAPSIS- 4500. KM ALT PERIAPSIS- 144. KM ALT INCLINATION- 90. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, FS=PROJECT SCIENTIST)

SPACECRAFT BRIEF DESCRIPTION THIS SATELLITE WILL CARRY EIGHT COMPLEMENTARY TYPES OF EXPERIMENTS, DESIGNED TO STUDY ATMOSPHERIC DENSITY AND ITS CHANGES AT LOW ALTITUDES. THE SATELLITE WILL BE SPIN STABILIZED, WITH THE SPIN AXIS PERPENDICULAR TO ITS POLAR ORBIT. W-EN THE ORBIT IS INCLINED MORE THAN 70 DEG, PERIGEE MOTION WILL BE LIMITED TO LESS THAN 2 DEG PER DAY. ORBIT PRECESSION, WHEN THE URBIT IS INCLINED MORE THAN 70 DEG9 WILL BE LIMITED TO LESS THAN 0.5 DEG PER DAY. THIS WILL LIMIT OBSERVATIONS FOR SAMPLING TO LESS THAN ONE-FOURTH OF THE POSSIBLE 24 HRS OF LOCAL SOLAR TIME.

*#*#******4*i********************************SOLAR MAXIMUM MISSION **************

SPACECRAFT COMMON NAME- SOLAR MAXIMUM MISSION ALTERNATE NAMES- SMM NSSDC ID- SMM

LAST REPORTED STATE- A PROPOSED MISSION

PLANNED LAUNCH DATE- MID 1978 SPACECRAFT WEIGHT IN ORBIT- 1300. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- go90. MIN APOAPSIS- 6828. KM ALT PERIAPSIS- 6828. KM ALT INCLINATION- 28. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGERo PS=PROJECT SCIENTIST) PS - So JORDAN NASA-GSFC GREENBELTo MD

SPACECRAFT BRIEF DESCRIPTION

1042 THE SCIENTIFIC OBJECTIVE OF THIS MISSION IS THE STUDY OF SOLAR FLARES AND FLARE-RELATED PHENOMENA. THE SPACECRAFT WILL BE POINTED AT THE SUN CONTINUOUSLY DURING THE DAYLIGHT PORTION OF THE ORBIT. IT WILL BE SPACE-SHUTTLE-COMPATIBLE TO ALLOW THE CAPABILITY OF RETRIEVING THE SPACECRAFT, REFITTING AND REFURBISHING IT. AND RETURNING IT TO ORBIT. THE SPACECRAFT WILL BE OPERATED BY A SOLAR CBSERVATORY OPERATIONS CENTER LOCATED AT THE GODDARD SACE FLIGHT CENTER* GREENEELT, MARYLAND. A SUBSTANTIAL GUEST INVESTIGATOR PROGRAM WILL BE SCHEDULED. TO ALLOW BROAD PARTICIPATION BY THE SCIENTIFIC COMMUNITY.

*****************+*##*****S******** 1A *************

SPACECRAFT COMMON NAME- SOLRAD IIA ALTERNATE NAMES- SRD-11A* SOLRAD HI-TRIP. SESP NC.NRL-111-0264, NRL-111 NSSDC ID- SRD-1IA

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 03/00/75 SPACECRAFT WEIGHT IN CRBIT- 102.15 KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- TITAN 3C

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-NAVY

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 3140. MIN APOAPSIS- 127622. KM ALT PERIAPSIS- 127622. KM ALT INCLINATION- 0. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - E.W. PETERKIN NAVAL RESEARCH LAB WASHINGTON, DC PS - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

SPACECRAFT BRIEF DESCRIPTION SOLRAD 11A WILL BE ONE OF A PAIR OF IDENTICAL SATELLITES THAT WILL BE PLACED IN A CIRCULAR EQUATORIAL ORBIT CF 20 EARTH RADII. THE SATELLITES, WHICH WILL BE ORIENTED TOWARDS THE SUN, WILL PROVIDE 100 PERCENT REAL-TIME. CONTINUOUS MONITORING OF SOLAR X-RAY* UV, AND ENERGETIC PARTICLE EMISSIONS. EXPERIMENTS WILL INCLUDE BROACBAND ION CHAMBERS OBSERVING SOLAR X RAYS BETWEEN 0.1 AND 60 A, PROPORTIONAL COUNTERS AND SCINTILLATORS OBSERVING SOLAR X RAYS BETwEEN 2 AND 150 KEV. AN EUV DETECTCR COVERING THREE BANDS BETWEEN 170 AND 1000 As A VARIABLE RESOLUTION EBERT-FASTIE SPECTROMETER COVERING THE WAVELENGTH RANGE OF 1100 TO 1600 A (RESOLUTION - 1 TO 25 A). A SOLAR WIND MONITOR. SOLAR PROTON. ELECTRON. AND ALPHA PARTICLE MONITORS, TWO X-RAY POLARIMETERS (ONE UTILIZING BRAGG SCATTERING AND THE OTHER UTILIZING THOMPSON SCATTERING). A BRAGG SPECTROMETER OBSERVING MAGNESIUM-11 AND -12 LINES. A LARGE-AREA AURORAL X-RAY DETECTOR. AND A PASSIVELY COOLED SOLID-STATE X-RAY DETECTOR TO MEASURE BACKGRCUND X-RAY EMISSIONS.

***********SOLRAD 11A, BLAKE

EXPERIMENT NAME- SOLAR PROTONS NSSDC ID- SRD-11A-14

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTER INVESTIGATOR) pI - J.B. BLAKE AEROSPACE CORP EL SEGUNDO, CA

1043 0I - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTCN. DC

EXPERIMENT BRIEF DESCRIPTION A PAIR OF IDENTICAL SENSORS WILL EE MOUNTED ON THE SPACECRAFT* WITH ONE ON THE SOLAR-ORIENTED SURFACE (THIS EXPERIMENT) AND ONE ON THE ANTISOLAR SURFACE (EXPERIMENT SRO-IIA-23). EACH SENSOR WILL BE A TWO-ELEMENT COUNTER USING DISK-SHAPED SEMICONDUCTORS AS DETECTOR ELEMENTS, WITH SHIELDING MATERIAL IN FRCNT OF AND BETWEEN THE TWC DETECTOR ELEMENTS. THE DETECTOR ELEMENTS WILL EE CONNECTED TO CHARGE-SENSITIVE AMPLIFIERS. CCINCIDENCE AND PULSE ,HEIGHT ANALYSIS WILL BE USED TO SEPARATE PULSES PRODUCED BY 2-MEV PROTONS, 10-MEV PROTONS, 4.--MEV ALPHA PARTICLES, 7.5-MEV ALPHA PARTICLES, AND HEAVY NUCLEI (Z GREATER THAN E GREATER THAN 3 MEV PER NUCLEON). A COMPLETE SET OF DATA POINTS WILL BE OBTAINED EVERY 2 MINUTES.

************SOLRAD I1A, BLAKE

EXPERIMENT NAME- OMNIDIRECTIONAL PROTONS NSSDC ID- SRD-IIA-17

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOCR OI=CTFER INVESTIGATOR) PI - J.B. BLAKE AEROSPACE CORP EL SEGUNDO, CA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION ? THIS EXPERIMENT IS DESIGNED TO MEASURE SOLAR PROTONS AND ALPHA PARTICLES. A SET OF FIVE SMALL SILICON CUBICAL SEMICONDUCTOR DETECTORS WILL. BE USED TO SEPARATELY MEASURE THE OMNIDIRECTIONAL PROTON AND ALPHA PARTICLE FLUXES IN THE EKERGY/NUCLEON RANGES 5 TO 20, 10 TO 25, 20 TO 40# 50 TO 90, AND 100 TO 160 MEV. A TWO-ELEMENT SEMICONDUCTOR TELESCOPE WILL USE COINCIDENCE REQUIREMENTS AND PULSE HEIGHT ANALYSIS TO DETERMINE PROTON FLUXES IN FIVE DIFFERENTIAL ENERGY CHANNELS FROM 20 TO 500 KEV AND IN THREE INTEGRAL CHANNELS AT 0.5, 1, AND 1.5 MEV. THE 36 TO 74 KEV DATA AND THE I-MEV DATA WILL BE SECTORED INTO QUADRANTS WHILE THE REMAINING CHANNELS WILL YIELD SPIN-INTEGRATED DATA. THE INSTRUMENT WILL CONSIST OF A PHOTOMULTIPLIER TUBE VIEWING A THIN PLASTIC SCINTILLATOR FOIL. PULSE HEIGHT ANALYSIS WILL EE USED TO SEPARATE IONS INTO FIVE GROUPS (Z = I, 2, 6 TO 10. 12 TO 18. AND GREATER THAN 18). THE IONS WILL HAVE ENERGY THRESHOLDS OF 0.5 MEV/NUCLEON (Z - 1 AND 2) THROUGH 0.8 MEV/NUCLEON (Z ABOVE 18). THE Z=2 AND Z=6 THROUGH 10 DATA WILL BE SECTORED INTO FOUR QUADRANTS. THE REMAINING DATA WILL BE SPIN INTEGRATED. A COMPLETE SET OF MEASUREMENTS WILL BE MADE ONCE EVERY 2 MIN.

************SOLRAD 11A, BLAKE

EXPERIMENT NAME- ANTISOLAR PROTONS NSSDC ID- SRD-IIA-23

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - J.B. BLAKE AEROSPACE CORP EL SEGUNDOC CA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A PAIR OF IDENTICAL SENSORS WILL BE MOUNTED ON THE SPACECRAFT, WITH ONE ON THE ANTISOLAF SURFACE (THIS EXPERIMENT) AND ONE ON THE SOLAR-ORIENTED SURFACE (EXPERIMENT SRD-IIA-14). EACH SENSOR WILL BE A TWO-ELEMENT COUNTER

1044 TELESCOPE USING DISK-SHAPED SEMICONDUCTORS AS DETECTOR ELEMENTS, WITH SHIELDING MATERIAL IN FRONT OF AND .BETWEEN THE TWO DETECTOR ELEMENTS. THE DETECTOR ELEMENTS WILL BE CCNNECTED TO CHARGE-SENSITIVE AMPLIFIERS. COINCIDENCE AND PULSE HEIGHT ANALYSIS WILL BE USED TO SEPARATE PULSES PRODUCED BY 2-MEV PROTONS, 10-MEV PROTONS. 4.5-MEV ALPHA PARTICLES, 7.5-MEV ALPHA PARTICLES, AND HEAVY NUCLEI (Z GREATER THAN 2. E GREATER THAN 3 MEV PER NUCLEON). A COMPLETE SET OF DATA PCINTS WILL BE OBTAINED EVERY 2 MIN.

************SOLPAD 11A. BYRAM

EXPERIMENT NAME- STELLAR/AURORAL X RAYS NSSDC ID- SRD-11IA-16

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - E.T. BYRAM NAVAL RESEARCH LAB WASHINGTON, DC 0I - D.M. HORAN NAVAL RESEARCH LAB WASHINGTGN, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF THREE PROPORTIONAL COUNTERS SENSITIVE TO X RAYS BETWEEN 1 AND 8 A. THESE PROPORTIONAL COUNTERS WILL BE MOUNTED ON THE SIDE OF THE SATELLITE AND ORIENTED 45 DEG, 90 DEG. AND 135 DEG OFF THE SPIN AXIS. THE COUNTING CIRCUITS WILL BE CONTROLLED BY THE ROLL PERIOD AND SYNCHRONIZED TO THE STAR AND/OR EARTH PULSES SO THAT DATA SAMPLES CAN BE ASSOCIATED WITH PORTIONS OF THE SKY. THE STELLAR PCRTION OF THIS EXPERIMENT WILL BE ABLE TC MAP COSMIC X-RAY SOURCES AND WILL SWEEP THE ENTIRE CELESTIAL SPHERE IN ABOUT 3 MONTHS. THE AURORAL PORTION OF THE EXPERIMENT WILL BE DESIGNED TO MONITOR AURORAL X-RAY EMISSIONS FROM THE EARTH. THE STELLAR PORTION SAMPLING CYCLE WILL TAKE 16 MIN* WHILE THE AURORAL PORTION WILL REQUIRE 2 MIN FOR A SAMPLING CYCLE.

***+******SOLRAD 11A, DOSCHEK

EXPERIMENT NAME- T-CMSON X-RAY POLARIMETER NSSDC ID- SRD-IIA-10

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CThER INVESTIGATOR) P1 - G.A. DOSCHEK NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION INCIDENT SOLAR X RAYS WILL BE SCATTERED BY A BLOCK GF LOW-DENSITY MATERIAL SUCH AS LITHIUM, LITHIUM HYDRIDE, OR BERYLLIUM. POLARIZED X RAYS WILL BE PREFERENTIALLY SCATTERED WHILE NCO-POLARIZED X RAYS WILL BE SCATTERED ISOTROPICALLY. TWO PROPORTIONAL COUNTERS, EACH WITH A TWO-CHANNEL PULSE HEIGHT ANALYZER TO PROVIDE ENERGY RESOLUTION IN 2- TO IO0-KEV AND 10- TO 50-KEV BANDS, WILL BE MOUNTED ON OPPOSITE SIDES OF THE SCATTERING BLOCK. AS THE SATELLITE ROLLS. THE SCATTERING ELCCK AND THE DETECTORS WILL BE ROTATED WITH RESPECT TO THE PLANE OF POLARIZATION OF THE INCIDENT X RAYS. THE DATA WILL BE GRATED ELECTRONICALLY INTO ACCUMULATORS ASSOCIATED WITH 45-DEG SECTORS IN THE ROLL DIRECTION. CYCLIC PULSE-CCUNT VARIATIONS FROM SECTOR TO SECTOR WILL REVEAL POLARIZATION IF PRESENT. THE DATA FROM THE 45-DEG SECTORS WILL BE ACCUMULATED FOR AN INTEGRAL NUMBER OF SPINS DURING EACH 30-SEC SAMPLING CYCLE AND THEN READ CUT ON COMMAND. A RADIOACTIVE SOURCE WILL SWING OUT BETWEEN EACH DETECTOR AND THE SCATTERING BLOCK FOR CALIBRATION IN.FLIGHT.

1045 ************SOLRAO I1A, FELDMAN

EXPERIMENT NAME- 1175- TO 1800-A SOLAR UV SFECTROMETER NSSDC ID- SRD-IIA-Og

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - P.D. FELDMAN NAVAL RESEARCH LAB WASHINGTON. DC OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTCN. DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL USE A ROTATABLE GRATING, OPERATING IN FIRST ORDER TO MEASURE THE SOLAR ELECTROMAGNETIC SPECTRUM BETWEEN 1175 AND 1800 A. A PHUTOMULTIPLIER TUBE WILL DETECT RADIATION REFLECTED THROUGH AN OPTICAL SYSTEM FROM THE GRATING. TWO SCANNING RATES WILL BE AVAILABLE -- A FAST-RATE LOW-RESOLUTION MCODE THE ENTIRE 625-A RANGE WILL BE COVERED IN 93.75 SEC, USING 25-A SEGMENTS FOR EACH DATA SAMPLE, AND A SLOW-RATE HIGH-RESOLUTION MODE IN WHICH THE 625-A RANGE WILL BE COVERED IN 12.5 MIN * USING 3.125-A SEGMENTS.

************SOLRAD IIA, FRITZ

EXPERIMENT NAME- 15- TO 150-KEV SOLAR X-RAY MONITOR NSSOC ID- SRD-IIA-01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - G.G. FRITZ NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL USE A CESIUM IODIDE SCINTILLATOR SURROUNDED BY A PLASTIC SCINTILLATOR OPERATED IN ANTICOINCIDENCE TO SCREEN OUT BACKGROUND COUNTS. PULSE HEIGHT ANALYSIS WILL PROVIDE SOLAR SPECTRA IN THE RANGES FROM 15 TO 20. 2C TO 30. 30 TO 60, AND 60 TO 150 KEV. NORMALLY, DATA WILL BE TELEMETERED FROM EACH CHANNEL EVERY 7.5 SEC, ALTHCUGH AN OPTIONAL MODE WILL SELECT THE 20-TO-30-KEV CHANNEL FOR TRANSMISSION EVERY 1.875 SEC. INFLIGHT CALIBRATION WILL BE MADE USING A RADIOACTIVE SOURCE WHICH WILL SWING IN FRONT OF THE DETECTOR UPON COMMAND AND REMAIN THERE FOR A 2-MIN TELEMETRY CYCLE. THE OVERALL CETECTOR DESIGN IS THE SAME AS THAT USED ON SOLRAD 10. WITH IMPROVED ELECTRONICS.

************SOLRAD 11A, FRITZ

EXPERIMENT NAME- X-RAY BACKGROUND NSSDC ID- SRD-II1A-24

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CThER INVESTIGATOR) PI G.G. - FRITZ NAVAL RESEARCH LAB WASHINGTON, DC 01 - R. LUCKE NAVAL RESEARCH LAB WASHINGTON, DC OI - R.C. HENRY NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A SOLID-STATE DETECTOR (GERMANIUM OR LITHIUM-DRIFTED SILICON) WILL BE USED TO MEASURE THE GALACTIC X-RAY BACKGROUND IN THE 0.5- TO 20-KEV RANGE

1046 WITH AN ENERGY RESOLUTION OF BETTER THAN 0.3 KEV. TO REACH THE DESIRED 0.3-KEV ENERGY RESOLUTION9 THE DETECTOR MUST BE PASSIVELY COOLED TO 70- TO 100-DEG KELVIN. THE INSTRUMENT WILL BE WOUNTED ON THE ANTISOLAR SIDE OF THE SPACECRAFT, AND WILL SWEEP OUT A BAND NEARLY 20 DEG WIDE CENTERED NEAR THE ECLIPTIC PLANE AS THE SATELLITE MOVES AROUND THE SUN. THE DETECTOR OUTPUT WILL UNDERGO A 256-CHANNEL ANALYSIS TO PRODUCE THE ENERGY SPECTRUM. ALL 254 CHANNELS WILL BE READ OUT IN 16 MIN. A RADIOACTIVE SOURCE MOUNTED ON A SHUTTER WILL BE USED TO PROVIDE IN-FLIGHT CALIBRATION OF THE DETECTOR.

************SOLRAD 11A, KELLEY

EXPERIMENT NAME- PROTON-ALPHA TELESCOPE NSSOC ID- SRD-11IA-20

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - J.G. KELLEY AFCRL BEDFORD. MA 01 - L. KATZ AFCRL BEDFORD, MA 01 - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION TWO TOTALLY DEPLETED SILICON SURFACE BARRIER DETECTORS IN A COINCIDENCE TELESCOPE ARRANGEMENT WILL BE USED TO DETECT I-TO 100-MEV PROTONS AND 10-TO 100-MEV ALPHA PARTICLES. PULSE HEIGHT ANALYSIS AND SUITABLE LOGIC ELEMENTS WILL BE USED TO PROVIDE 11 PROTON CHANNELS AND FOUR ALPHA PARTICLE CHANNELS. THE TELESCOPE WILL BE INSENSITIVE TO LIGHT AND TO ELECTRONS. VERY LITTLE FLUX DIRECTIONALITY INFORMATION WILL BE OBTAINED.

************SOLRAD l1At KELLEY

EXPERIMENT NAME- LOW-ENERGY PROTON SPECTROMETER NSSDC ID- SRD-11A-21

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - J.G. KELLEY AFCRL BEDFORD, MA OI - L. KATZ AFCRL BEDFORD, MA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION TWO TOTALLY DEPLETED SILICON SURFACE BARRIER DETECTORS MOUNTED IN A SERIES WILL MEASURE PROTONS BETWEEN 150 KEV AND 6 MEV. PULSE HEIGHT ANALYSIS OF PULSES GENERATED IN THE FRONT DETECTOR, WHICH ARE UNACCOMPANIED BY PULSES IN THE REAR DETECTOR* WILL SEPARATE THE PROTON COUNTS INTO 12 ENERGY CHANNELS. PERMANENT MAGNETS WILL BE USED TO DEFLECT AWAY INCIDENT ELECTRONS WITH ENERGIES LESS THAN 2 MEV. VERY LITTLE FLUX DIRECTIONALITY INFORMATION WILL BE OBTAINEC.

************SOLRAD 11A, KREPLIN

EXPERIMENT NAME- 1- TO 8-A SOLAR X-RAY MONITOR NSSDC ID- SRD-I1A-04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR)

1047 PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC 01 - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO COMPLETE SETS OF IONIZATION-CHAMBER AND ELECTROMETER-AMPLIFIER COMBINATIONS. THE IONIZATION CHAMBERS WILL BE SENSITIVE TO SOLAR X RAYS IN THE 1- TO 8-A RANGE. THE TWO SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES. ALTHOUGH CNLY ONE SET WILL BE SELECTED FOR TELEMETRY TRANSMISSION. DATA WILL BE TRANSMITTED WITH A 15-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIERS WILL BE ABLE TO CHANGE RANGES AUTOMATICALLY OR MANUALLY. THE DETECTORS CANNOT BE CALIBRATED IN FLIGHT BUT THE ELECTROMETER-AMPLIFIERS MAY BE CALIERATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR.

************SOLRAD 11A. KREPLIN

EXPERIMENT NAME- 8- TO 16-A SOLAR X-RAY MONITOR NSSDC I-- SRD-1IA-05

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO COMPLETE SETS OF IONIZATION-CHAMEER AND ELECTROMETER-AMPLIFIER COMBINATIONS. THE IONIZATION CHAMBERS WILL BE SENSITIVE TO SOLAR X RAYS IN THE 8- TO 16-A RANGEo THE TWO SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES* ALTHOUGH ONLY ONE SET WILL BE SELECTED FOR TELEMETRY TRANSMISSION. DATA WILL BE TRANSMITTED WITH A 30-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIERS WILL BE ABLE TO CHANGE RANGES AUTOMATICALLY OR MANUALLY. THE DETECTORS CANNOT BE CALIBRATED IN FLIGHT, BUT THE ELECTROMETER-AMPLIFIERS MAY BE CALIERATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR.

************SOLRAO 11A, KREPLIN

EXPERIMENT NAME- 44- TO 60-A SOLAR X-RAY MONITOR NSSDC ID- SRD-1A-06

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 01 - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC OI - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO COMPLETE SETS OF IONIZATION-CHAMEER AND ELECTROMETER-AMPLIFIER COMBINATIONS. THE IONIZATION CHAMBERS WILL BE SENSITIVE TO SOLAR X-RAYS IN THE 44- TO 60-A RANGE. THE TWO SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES, ALTHOUGH ONLY ONE SET WILL BE SELECTED FOR TELEMETRY TRANSMISSION. DATA WILL BE TRANSMITTED WITH A 30-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIERS WILL BE ABLE TO CHANGE RANGES AUTOMATICALLY OR MANUALLY THE ELECTROMETER-AMPLIFIERS MAY BE CALIBRATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR. THE DETECTORS CAN

1048 SOURCE BE CALIBRATED IN FLIGHT BY COMMANDING A SHUTTER-MOUNTED RADIOACTIVE INTO POSITION.

************SOLRAD 1LA, KREPLIN

EXPERIMENT NAME- 170- TO 1050-A SOLAR EUV MONITOR NSSDC ID- SRD-11IA-07

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC 01 - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF THREE SETS OF LITHIUM-FLUORIDE PHOTOSENSITIVE SURFACE DETECTORS COUPLED TO FOUR-RANGE TO THE ELECTROMETER-AMPLIFIERS. THE THREE SETS.WILL NOT BE REDUNDANT DUE DIFFERENT FILTERS BEING USED. A BERYLLIUM FILTER WILL LIMIT ONE DETECTOR'S A SECOND RESPONSE TO WAVELENGTHS FROM 170 TO 500 A. A TIN FILTER WILL LIMIT DETECTOR'S RESPONSE TO WAVELENGTHS FROM 450 TO 850 A. AN INDIUM FILTER WILL LIMIT THE THIRD DETECTOR'S RESPONSE TO WAVELENGTHS FROM 725 .TO 1050 A. THE DETECTOR-ELECTROMETER SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES. EACH DETECTOR WILL EE READ EVERY 7.5 SEC. THE ELECTROMETERS MAY BE CALIBRATED DURING FLIGHT WITHOUT DETACHING THE DETECTOR ALTHOUGH THE DETECTORS CANNOT BE CALIBRATED IN FLIGHT.

t***********SOLRAD 11A KREFLIN

EXPERIMENT NAME- 1080- TO 1350-A SOLAR UV MONITOR NSSDC ID- SRD-IIA-Oe

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 0I - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC 01 - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF ONE 4-RANGE ELECTROMETER-AMPLIFIER AND THE THREE IONIZATION CHAMBERS. TWO OF THE IONIZATION CHAMBERS WILL BE THESE STANDARD GAS-FILLED CHAMBERS FLOWN ON PREVIOUS SOLRAD SATELLITES. DETECTORS. ELECTRONICALLY AND MECHANICALLY PAIREO, WILL BE DESIGNATED AS WITH DETECTOR 'A'. THE THIRD IONIZATION CHAMBER WILL BE AN EVACUATED CHAMBER A LITHIUM FLUORIDE PHOTOSENSITIVE SURFACE* AND WILL BE DESIGNATED AS FOR DETECTOR 'B'. NORMALLY, DETECTOR B WILL BE CONTINUOUSLY SELECTED A FOR TELEMETRY TRANSMISSION AND WILL BE REPLACED ONLY OCCASIONALLY BY CALIBRATING B AND EXPERIMENT 9. A MECHANICAL SHUTTER, MOVABLE BY COMMAND, CAN EE WILL SHIELD THE WINDOW OF 8A FROM THE SUN. THE ELECTROMETER-AMPLIFIER DATA CALIBRATED WITHOUT DETACHING THE DETECTOR FROM THE DETECTOR SYSTEM. WILL BE SAMPLED AT 15-SEC INTERVALS.

*****#******SOLRAD IIA, KREPLIN

EXPERIMENT NAME- 0.5- TO 3-A SOLAR X-RAY MONITOR NSSDC ID- SRD-IIA-12

1049 LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC 01 D.M. - HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF THREE IONIZATION CHAMBERS CONNECTED IN PARALLEL TO A SINGLE ELECTROMETER-AMPLIFIER. THE IONIZATION CHAMBERS WILL BE SENSITIVE TO SOLAR X RAYS IN THE 0.5- TC 3.0-A RANGE. DATA WILL BE TRANSMITTED WITH A 15-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIER WILL BE ABLE TO CHANGE CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE DETECTORS CANNOT BE CALIBRATED IN FLIGHT, BUT THE ELECTROIETER-AMPLIFIER MAY BE CALIBRATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR.

********SOLRAD 11A. KREPLIN

EXPERIMENT NAME- 1- TO 20-A SOLAR X-RAY MONITOR NSSDC ID- SRD-11A-13

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF AN IONIZATION CHAMBER AND ONE ELECTROMETER-AMPLIFIER. THE IONIZATION CHAMBER WILL BE SENSITIVE TO SOLAR X-RAYS IN THE I-TO 20-A RANGE. DATA WILL BE TRANSMITTED WITH A 30-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIER WILL BE ABLE TO CHANGE CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE DETECTOR CANNOT BE CALIBRATED IN FLIGHT, BUT THE ELECTROMETER-AMPLIFIER MAY BE CALIBRATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR.

***********SOLRAD 1IA9 MEEKINS

EXPERIMENT NAME- CONTINUUM (8.8 A) AND MAGNESIUM LINE (9.17 A AND 8.42 A) MONITOR NSSDC ID- SRD-1-A-03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - J.F MEEKINS NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION SOLAR X RAYS WILL BE OBSERVED IN THE MAGNESIUM-11 AND-13 LINES (9.17 AND 8.42 A A) AND IN THE CONTINUUM AT 8.8 A. THREE SHA CRYSTALS FIXED AT THREE DIFFERENT ANGLES WILL ALLOW SOLAR X RAYS TO UNDERGO FIRST-ORCER BRAGG REFLECTION INTO THREE PROPORTIONAL COUNTERS. SHOULD THE SPACECRAFT SPIN AXIS BECOME IMPROPERLY ORIENTED, THE SPECTROMETER WOULD FUNCTICN PROPERLY IF THE ASPECT ANGLE WERE NO MORE THAN I DEG OFF NOMINAL. ALTHOUGH THE INSTRUMENT WOULD THEN FUNCTION AS A SCANNING SPECTROMETER WITH AN EXTREMELY SMALL SPECTRAL RANGE IN THE VICINITY OF THE TARGET WAVELENGTHSO DATA WILL BE ACCUMULATED OVER INTERVALS OF 1/64 OF A SPACECRAFT~S SPIN PERIODo AND THE

1050 EXPERIMENT WILL HAVE A SAMPLING CYCLE OF APPROXIMATELY I-MIN DURATION.

************SOLRAD 11A, MEEKINS

EXPERIMENT NAME- BRAGG X-RAY POLARIMETER NSSDC ID- SRD-1IA-11

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR* OI=CTHER INVESTIGATOR) PI - J.F. MEEKINS NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE A LITHIUM FLUORIDE CRYSTAL, FIXED AT AN ANGLE TO ALLOW SOLAR X RAYS OF ABOUT 2.8 A TO UNDERGO FIRST-ORDER BRAGG REFLECTION INTO A PROPORTIONAL COUNTER. SINCE THE REFLECTION CF POLARIZED RADIATION DEPENDS UPON THE ANGLE BETWEEN THE ELECTRIC VECTOR OF THE RADIATION AND THE REFLECTING ANGLE OF THE CRYSTAL, THE SPIN OF THE SATELLITE WILL MODULATE THE INTENSITY OF REFLECTED POLARIZED RADIATION. DATA PULSES ASSOCIATED WITH 45-DEG SECTORS IN THE ROLL DIRECTION WILL BE ELECTRONICALLY GRATED INTO CORRESPONDING ACCUMULATORS. SIGNAL VARIATIONS FROM SECTOR TO SECTOR WILL INDICATE THE PRESENCE OF POLARIZED RADIATION. DATA FOR EACH 45-DEG SECTOR WILL EE ACCUMULATED FOR AN INTEGRAL NUMBER OF SPINS AND READ OUT ONCE IN EACH 2-MIN TELEMETRY CYCLE.

************SOLRAD liA, SMATHERS

EXPERIMENT NAME- X-RAY MONITOR (0.1-1.6 A. 0.5-3 A. 1-4 A) NSSDC ID- SRD-11A-02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - H.W. SMATHERS NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION FOUR ELECTRONICALLY PAIRED GAS-FILLED PROPORTIONAL COUNTERS WILL BE USED TO MEASURE X-RAY EMISSION BETWEEN 4 AND 100 KEV IN FOUR CHANNELS. ALL FOUR DETECTORS WILL HAVE 10-MIL BERYLLIUM WINDOWS PLUS ADDITIONAL ALUMINUM OR BERYLLIUM MATERIAL MOUNTED IN FRONT CF THE DETECTORS. EACH DETECTOR WILL BE SAMPLED ONCE EVERY 7.5 SEC. ALTHOUGH AN OPTIONAL MODE WILL TRANSMIT DATA FROM ONLY ONE OR TWO DETECTORS. EFFECTIVELY QUADRUPLING OR DOUBLING THE SAMPLING RATE OF THAT DETECTOR. IN-FLIGHT CALIBRATION WILL BE PERFORMED USING A RADIOACTIVE SOURCE WHICH CAN BE MOVED IN FRONT OF THE DETECTORS UPON COMMAND.

************SOLRAD IIA, VAMPOLA

EXPERIMENT NAME- SCLAR FLARE ELECTRONS NSSDC ID- SRD-IIA-22

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - A.L. VAMPOLA AEROSPACE CORP EL SEGUNDO. CA 01 - J.B. BLAKE AEROSPACE CCRP EL SEGUNDC, CA 01 - R.W . KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC

1051 EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL MEASURE SOLAR ELECTRONS. TWO PERMANENT MAGNETS WILL BE USED TO MOMENTUM-ANALYZE INCIDENT ELECTRONS. ARRAYS OF SILICON DETECTORS WILL COUNT INCIDENT ELECTRONS IN 12 ENERGY CHANNELS FROM 11 KEV TO 1.5 MEV. SPIN-INTEGRATED DATA WILL BE OBTAINED ONCE EVERY 2 MINs EXCEPT THAT 11--.%EV AND 405-KEV DATA WILL BE SECTORED INTO QUADRANTS, AND 60-KEV AND 610-KEV DATA WILL BE OBTAINED WITH 15-SEC RESOLUTION,

************SOLRAD 11A, %ELLER, JR.

EXPERIMENT NAME- GEOCORONAL-EXTRATERRESTRIAL EUV - DETECTOR I NSSDC ID- SRD-11A-le

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINC'IPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - C.S. WELLER, JR. NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A COLLIMATED CHANNELTRON PHOTOMULTIPLIER MOUNTED BEHIND A FILTER WHEEL WILL BE USED TO MEASURE EUV RADIATION FRCN NON-SOLAR SOURCES. THE FILTER WHEEL WILL ALLOW VARIOUS EMISSION LINES BETWEEN 200- AND 1400-A TO BE ISOLATED, AS WELL AS ALLOWING IN-FLIGHT CALIBRATION THROUGH THE USE OF A RADIOACTIVE SOURCE. THE DETECTOR WILL BE MOUNTED TO LOOK 90 DEG OFF THE SPIN AXIS OF THE SPACECRAFT AND WILL SWEEP THE CELESTIAL SPHERE IN ABOUT SIX MONTHS. EACH DATA SAMPLE WILL BE ACCUMULATED OVER INCREMENTS OF 1/64 OF THE SPACECRAFT'S SPINs WITH THE SAMPLE SOURCE REFERENCED TO EITHER A STAR PULSE OR THE EARTH PULSE. THE DATA WILL BE READ OUT IN 2-MIN INTERVALS. THIS EXPERIMENT IS NCT EXPECTED TO BE OPERATED MORE THAN 1 HR PER DAY.

************SOLRAD 11A WELLER, JR.

EXPERIMENT NAME- GEOCORONAL-EXTRATERRESTRIAL EUV - DETECTOR 2 NSSDC ID- SRD-I1A-19

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR OI=OTHER INVESTIGATOR) PI - C.S. WELLER, JR. NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION A COLLIMATED CHANNELTRON PHOTOMULTIPLIER MOUNTED BEHIND A FILTER WHEEL WILL BE USED TO MEASURE EUV RADIATION FROM NON-SOLAR SOURCES. THE FILTER WHEEL WILL ALLOW VARIOUS EMISSION LINES BETWEEN 200-AND 1400 -A TO BE ISOLATED. AS WELL AS ALLOWING IN-FLIGHT CALIBRATION THROUGH THE USE OF A RADIOACTIVE SOURCE. THE DETECTOR WILL BE MOUNTED TO LOOK 90 DEG OFF THE SPIN AXIS OF THE SPACECRAFT AND WILL SWEEP THE CELESTIAL SPHERE IN ABOUT 6 MONTHS. EACH DATA SAMPLE WILL BE ACCUMULATED OVER INCREMENTS OF 1/64 OF THE SPACECRAFT'S SPIN* WITH THE SAMPLE SOURCE REFERENCED TO EITHER A STAR PULSE OR THE EARTH PULSE. THE DATA WILL BE READ OUT IN 2-MIN INTERVALS. THIS EXPERIMENT IS NCT EXPECTED TO BE OPERATED MORE THAN 1 HR PER DAY.

**** * **####**** #*##+** ***SOLRAD 11E * ** *****I

SPACECRAFT COMMON NAME- SOLRAD 118

1052 ALTERNATE NAMES- SOLRAD HI-TRIP, NRL-1119 PL-723F, SESP NO.NRL-llI-0264, SOLRAD NSSDC ID- SRD-118

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 03/00/75 SPACECRAFT WEIGHT IN ORBIT- 102.15 KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- TITAN 3C

SPONSORING COUNTRY/AGENCY UNITED STATES DOD-NAVY

PLANNED ORBIT PARAMETERS ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- 3140. MIN APOAPSIS- 127622. KM ALT PERIAPSIS- 127e22. KM ALT INCLINATION- 0. DEG

SPACECRAFT PERSONNEL (FM=PROJECT MANAGER, FS=PROJECT SCIENTIST) PM - E.W. PETERKIN NAVAL RESEARCH LAB WASHINGTON. DC PS - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTCN, DC

SPACECRAFT BRIEF DESCRIPTION SOLRAD lie WILL BE ONE OF A PAIR CF IDENTICAL.SATELLITES THAT WILL BE PLACED IN A CIRCULAR EQUATORIAL ORBIT OF 20 EARTH RADII. THE SATELLITES. WHICH WILL BE ORIENTED TOWARD THE SUN, WILL PROVIDE 100 PERCENT REAL-TIME. CONTINUOUS MONITORING OF SOLAR X-RAY, UV, AND ENERGETIC PARTICLE EMISSIONS. EXPERIMENTS WILL INCLUDE BROADBAND ION CHAMBERS OBSERVING SOLAR X RAYS BETWEEN-0.1 AND 60 A, PROPORTIONAL COUNTERS AND SCINTILLATORS OBSERVING SOLAR X RAYS BETWEEN 2 AND 150 KEV, AN EUV DETECTOR COVERING THREE BANDS BETWEEN 170 AND 1000 A, A VARIABLE RESOLUTION EBERT-FASTIE SPECTROMETER COVERING THE WAVELENGTH RANGE OF 1100 TO 1600 A (RESOLUTION - 1 TO 25 A), A SOLAR WIND MONITOR, SOLAR PROTON, ELECTRON. AND ALPHA PARTICLE MONITORS. TWO X-RAY POLARIMETERS (ONE UTILIZING BRAGG SCATTERING AND THE OTHER UTILIZING THOMPSON SCATTERING), A BRAGG SPECTROMETER OBSERVING MAGNESIUM-11 AND -12 LINES, A LARGE-AREA AURORAL X-RAY DETECTOR, AND A PASSIVELY COOLED SOLID-STATE X-RAY DETECTOR TO MEASURE BACKGROUND X-RAY EMISSIONS.

************SOLRAD 118, ELAKE

EXPERIMENT NAME- SOLAR PROTONS NSSDC ID- SRD-11B-14

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - J.B. BLAKE AEROSPACE CORP EL SEGUNDO, CA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A PAIR OF IDENTICAL SENSORS WILL BE MOUNTED ON THE SPACECRAFT* WITH ONE ON THE SOLAR-ORIENTED SURFACE (THIS EXPERIMENT) AND ONE ON THE ANTISOLAR SURFACE (EXPERIMENT SRD-11B-23). EACH SENSOR WILL BE A TWO-ELEMENT COUNTER TELESCOPE USING DISK-SHAPED SEMICONDUCTCRS AS DETECTOR ELEMENTS, WITH SHIELDING MATERIAL IN FRONT OF AND BETWEEN THE TWO DETECTOR ELEMENTS. THE DETECTOR ELEMENTS WILL BE CONNECTED TO CHARGE-SENSITIVE AMPLIFIERS. COINCIDENCE AND PULSE HEIGHT ANALYSIS WILL BE USED TO SEPARATE PULSES PRODUCED BY 2-MEV PROTONS, 10-MEV PROTONS, 4.5-MEV ALPHA PARTICLES, 7.5-MEV ALPHA PARTICLES, AND HEAVY NUCLEI (Z GREATER THAN 2, E GREATER THAN 3 MEV PER NUCLEON). A COMPLETE SET OF DATA POINTS WILL BE OBTAINED EVERY 2 MIN.

1053 ************SOLRAD 118, BLAKE

EXPERIMENT NAME- OMNIDIRECTIONAL PROTONS NSSDC ID- SRD-IB--17

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - J.B. BLAKE AEROSPACE CORP EL SEGUNDO. CA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTGON OC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL BE ABLE TO MEASURE SOLAR PROTONS AND ALPHA PARTICLES. A SET OF FIVE SMALL SILICON CUBICAL SEMICONDUCTOR DETECTORS WILL BE USED TO SEPARATELY MEASURE THE OMNIDIRECTIONAL PROTON ANC ALPHA PARTICLE FLUXES IN THE ENERGY/NUCLEON RANGES 5 TC 20 10 TO 25. 20 TO 40. 50 TO 90, AND 100 TO 160 MEV. A TWO-ELEMENT SEMICONDUCTOR TELESCOPE WILL USE COINCIDENCE REQUIREMENTS AND PULSE HEIGHT ANALYSIS TO DETERMINE PROTON FLUXES IN FIVE DIFFERENTIAL ENERGY CHANNELS FROM 20 TO 500 KEV AND IN THREE INTEGRAL CHANNELS AT 0.5. 1. AND 1.5 MEV. THE 36-TO 74-KEV AND THE I-MEV DATA WILL BE SECTORED INTO QUADRANTS WHILE THE REMAINING CHANNELS WILL YIELD SPIN-INTEGRATED DATA. THE INSTRUMENT WILL CONSIST OF A PHOTOMULTIPLIER TUBE VIEWING A THIN PLASTIC SCINTILLATOR FOIL. PULSE HEIGHT ANALYSIS WILL BE USED TO SEPARATE IONS INTO FIVE GROUPS -- Z EQUAL TO I, 2, 6 TO 10* 12 TO 18. AND GREATER THAN 18. THE IONS WILL HAVE ENERGY THRESHOLDS OF 0.5 MEV/NUCLEON (Z EQUAL TO I OR 2) THROUGH 0.8 MEV/NUCLEON (Z GREATER THAN 18). THE Z=2 AND Z=6 THROUGH 10 DATA WILL BE SECTORED INTO FOUR QUADRANTS. THE REMAINING DATA WILL BE SPIN INTEGRATED. A COMPLETE SET OF MEASUREMENTS WILL BE MADE ONCE EVERY 2 MIN.

************SOLRAD 118, BLAKE

EXPERIMENT NAME- ANTISOLAR PROTONS NSSDC ID- SRD-11B-23

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - J.8. BLAKE AEROSPACE CORP EL SEGUNDO, CA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A PAIR OF IDENTICAL SENSORS WILL BE MOUNTED ON THE SPACECRAFT, ONE ON THE ANTISOLAR SURFACE (THIS EXPERIMENT) AND ONE ON THE SOLAR-ORIENTED SURFACE (EXPERIMENT SRD-118-14). EACH SENSOR WILL BE A TWO-ELEMENT COUNTER TELESCOPE USING DISK-SHAPED SEMICONDUCTORS AS DETECTOR ELEMENTS. WITH SHIELDING MATERIAL IN FRONT OF AND BETWEEN THE TWO DETECTOR ELEMENTS. THE DETECTOR ELEMENTS WILL BE CONNECTED TO CHARGE-SENSITIVE AMPLIFIERS. COINCIDENCE ANALYSIS AND PULSE HEIGHT-ANALYSIS WILL BE USED TO SEPARATE PULSES PRODUCED BY 2-MEV PROTONS I0--MEV PROTONS, 4.5-MEV ALPHA PARTICLES9 7.5-MEV ALPHA PARTICLES* AND HEAVY NUCLEI (Z GREATER THAN 2), WITH E GREATER THAN 3 MEV PER NUCLEON. A COMPLETE SET OF DATA POINTS WILL BE OBTAINED EVERY 2 MINUTES.

**********SSOLRAD 118 BYRAM

EXPERIMENT NAME- STELLAR/AURORAL X-RAYS

1054 NSSDC ID- SRD-1IB-16

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - E.T. BYRAM NAVAL RESEARCH LAB WASHINGTON. DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF THREE PROPORTIONAL COUNTERS SENSITIVE TO X RAYS BETWEEN I AND 8 A. THESE PROPORTIONAL COUNTERS WILL BE MOUNTED ON THE SIDE OF THE SATELLITE AND ORIENTED 45 DEG* 90 DEG. AND 135 DEG OFF THE SPIN AXIS. THE CCUNTING CIRCUITS WILL BE COCNTROLLEO BY THE ROLL PERfOD AND SYNCHRONIZED TO THE STAR AND/OR EARTH PULSES SO DATA SAMPLES CAN BE ASSOCIATED WITH PCRTICNS OF THE SKY. THE STELLAR PORTION OF THIS EXPERIMENTWILL EE ABLE TO MAP COSMIC X-RAY SOURCES AND SWEEP THE ENTIRE CELESTIAL SPHERE IN ABOUT6X MONTHS. THE AURORAL PORTION OF THE EXPERIMENT IS DESIGNED TO MONITOR AURORAL X-RAY EMISSIONS FROM THE EARTH. THE STELLAR PORTION SAMPLING CYCLE WILL REQUIRE 16 MIN WHILE THE AURORAL PORTION WILL REQUIRE TWO MINUTES FOR A SAMPLING CYCLE.

************SOLRAD 116, DOSCHEK

EXPERIMENT NAME- THOMSON X-RAY POLARIMETER NSSDC ID- SRD-1IB-10

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - G.A. DOSCHEK NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION INCIDENT SOLAR X-RAYS WILL BE SCATTERED BY A BLOCK OF LOW-DENSITY MATERIAL SUCH AS LITHIUM. LITHIUM HYDRIDE, OR BERYLLIUM. POLARIZED XRAYS WILL BE PREFERENTIALLY SCATTERED WHILE NON-POLARIZED X RAYS WILL BE SCATTERED ISOTROPICALLY. TWO PROPORTIONAL COUNTERS. EACH WITH TWO-CHANNEL PULSE HEIGHT ANALYZERS TO PROVIDE ENERGY RESOLUTICN IN 2- TO IO-KEV AND 10- TO SO-KEV BANDS, WILL BE MOUNTED ON OPPOSITE SIDES OF THE SCATTERING BLOCK. AS THE SATELLITE ROLLS, THE SCATTERING BLOCK AND THE DETECTORS WILL BE ROTATED WITH RESPECT TO THE PLANE OF POLARIZATION OF THE INCIDENT X RAYS. THE DATA WILL BE GATED ELECTRONICALLY INTO ACCUMULATORS ASSOCIATED WITH 45-DEG SECTORS IN THE ROLL DIRECTION. CYCLIC PULSE-COUNT VARIATIONS FROM SECTOR TO SECTOR WILL REVEAL POLARIZATION IF PRESENT. THE DATA FROM THE 45-DEG SECTORS WILL BE ACCUMULATED FOR AN INTEGRAL NUMBER OF SPINS DURING EACH 30-SEC SAMPLING CYCLE AND THEN READ OUT ON COMMAND. A RADIOACTIVE SOURCE WILL SWING OUT BETWEEN EACH DETECTOR AND THE SCATTERING BLOCK FOR CALIBRATION IN FLIGHT.

***4********SOLRAD 118. FELDMAN

EXPERIMENT NAME- 1175- TO 1800-A SOLAR UV SPECTROMETER NSSOC ID- SRD--1I18-09

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) P1 - p.O. FELDMAN NAVAL RESEARCH LAB WASHINGTONs DC 01 - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

1055 EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL USE A ROTATABLE GRATING, OPERATING IN FIRST ORDER TO MEASURE THE SOLAR ELECTROMAGNETIC SPECTRUM BETWEEN 1175 AND 1800 A. A PHOTOMULTIPLIER TUEE WILL DETECT RADIATION REFLECTEC THRCUGH AN OPTICAL SYSTEM FROM THE GRATING. TWO SCANNING RATES WILL BE AVAILABLE -- A FAST-RATE LOW RESOUTION MODE IN WHICH ThE ENTIRE e25-A RANGE WILL BE COVERED IN 93.75 SECONDS, USING 25-A SEGMENTS FOR EACH DATA SAMPLE* AND A SLCW-RATE HIGH-RESOLUTION MODE IN WHICH THE 625 -A RANGE WILL BE COVERED IN 12.5 MINUTES, USING 3.12E-A SEGMENTS.

************SOLRAD 118 FRITZ

EXPERIMENT NAME- 15- TO 150-KEV SOLAR X-RAY MONITOR NSSDC ID- SRD-11B-01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - G.G. FRITZ NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL USE A CESIUM IODIDE SCINTILLATOR SURROUNDED BY A PLASTIC SCINTILLATOR OPERATED IN ANTICOINCIDENCE TO SCREEN OUT BACKGROUND COUNTS. PULSE HEIGHT ANALYSIS WILL PROVIDE SOLAR SPECTRA IN THE RANGES FROM 15 TO 20, 20 TO 30, 30 TO 60. AND 60 TO 150 KEV. NORMALLY. DATA WILL BE TELEMETERED FROM EACH CHANNEL EVERY 7.5 SEC. ALTHOUGH AN OPTIONAL MODE CAN SELECT THE 20 -C 30-KEV CHANNEL FOR TRANSMISSION EVERY 1.875 SEC. IN-FLIGHT CALIBRATION WILL BE MADE USING A RADIOACTIVE SOURCE WHICH WILL SWING IN FRONT OF THE DETECTOR UPON COMMAND AND REMAIN THERE FOR A 2-MIN TELEMETRY CYCLE. THE OVERALL CESIGN IS THE SAME AS THAT USED ON SCLRAO 10, WITH IMPROVED ELECTRONICS.

************SOLRAD 118. FRITZ

EXPERIMENT NAME- X-RAY BACKGROUND NSSDC ID- SRD-11B-24

LAST REPORTEU STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - G.G. FRITZ NAVAL RESEARCH LAB WASHINGTON. DC OI - R. LUCKE NAVAL RESEARCH' LAB WASHINGTON, DC 01 - R.C. HENRY NAVAL RESEARCH LAB WASHINGTON* DC

EXPERIMENT BRIEF DESCRIPTION A SOLID-STATE DETECTOR (GERMANIUM OR LITHIUM-DRIFTED SILICON) WILL BE USED TO MEASURE THE GALACTIC X-RAY BACKGROUND IN THE 0.5- TO 20-KEV RANGE WITH AN ENERGY RESOLUTION OF BETTER THAN 0.3 KEV. TC REACH THE DESIRED O.3-KEV ENERGY RESOLUTION, THE DETECTOR MLST BE PASSIVELY COOLED TO 70- TO 100-DEG KELVIN. THE INSTRUMENT WILL BE MOUNTED ON THE ANTISOLAR SIDE OF THE SPACECRAFT AND WILL SWEEP OUT A BAND NEARLY 20-DEG WIDE CENTERED NEAR THE ECLIPTIC PLANE AS THE SATELLITE MOVES AROUND THE SUN. THE DETECTOR OUTPUT WILL UNDERGO 256-CHANNEL ANALYSIS TO PRODUCE THE ENERGY SPECTRUM. ALL 256 CHANNELS WILL BE READ OUT IN 16 MIN. A RADIOACTIVE SOURCE MOUNTED ON A SHUTTER WILL BE USED TO PROVIDE IN-FLIGHT CALIBRATION OF THE DETECTOR.

************SOLRAD 118, KELLEY

1056 EXPERIMENT NAME- PROTON-ALPHA TELESCOPE NSSDC ID- SRD-11B-2C

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) P1 - J.G. KELLEY AFCRL BEDFORD, MA OI - L. KATZ AFCRL BEDFORDO MA 01 - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION TWO TOTALLY DEPLETED SILICON SURFACE-BARRIER DETECTORS IN A COINCIDENCE TELESCOPE ARRANGEMENT WILL BE USED TO DETECT 1- TO 100-MEV PROTONS AND 10- TO 100-MEV ALPHA PARTICLES. PULSE HEIGHT ANALYSIS AND SUITABLE LOGIC ELEMENTS WILL BE USED TO PROVIDE 11 PROTON CHANNELS AND FOUR ALPHA PARTICLE CHANNELS, THE TELESCOPE WILL BE INSENSITIVE TO LIGHT AND TO ELECTRONS. VERY LITTLE FLUX DIRECTIONALITY INFORMATION WILL BE OBTAINED.

******#*****SOLRAD 11B. KELLEY

EXPERIMENT NAME- LOW-ENERGY PROTON SPECTROMETER NSSDC ID- SRD-IIB-21

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - J.G. KELLEY AFCRL BEDFORD, MA 01 - L. KATZ AFCRL BEDFCRO, MA OI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION TWO TOTALLY DEPLETED SILICON SURFACE BARRIER DETECTORS MOUNTED IN A SERIES WILL MEASURE PROTONS BETWEEN 150 KEV AND 6 MEV. PULSE HEIGHT ANALYSIS OF PULSES GENERATED IN THE FRONT DETECTOR WHICH ARE UNACCOMPANIED BY PULSES IN THE REAR DETECTOR WILL SEPARATE THE PROTON COUNTS INTO 12 ENERGY ELECTRONS CHANNELS. PERMANENT MAGNETS WILL BE USED TO DEFLECT AWAY INCIDENT wITH ENERGIES LESS THAN 2 MEV. VERY LITTLE FLUX DIRECTIONALITY INFORMATION WILL BE OBTAINEC.

************SOLFAD IiB, KREPLIN

EXPERIMENT NAME- 1- TO 8-A SOLAR X-RAY MONITOR NSSDC ID- SRD-11B-04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) DC P1 - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC OI - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO COMPLETE SETS OF IONIZATION/CHAMEER AND ELECTROMETER-AMPLIFIER COMBINATIONS. THE IONIZATION TWO CHAMBERS WILL eE SENSITIVE TO SOLAR X RAYS IN THE 1- TO 8-A RANGE. THE SET WILL SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES, ALTHOUGH ONLY ONE WITH A BE SELECTED FOR TELEMETRY TRANSMISSION. DATA WILL BE TRANSMITTED TO CHANGE 15-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIERS WILL BE ABLE

1057 CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE DETECTORS CANNOT BE CALIBRATED IN FLIGHTs BUT THE ELECTROMETER-AMPLIFIERS MAY BE CALIBRATED ON EACH RANGE WITHOUT DETACHING TI-E DETECTOR.

************SOLRAC 118, KREPLIN

EXPERIMENT NAME- 8- TO 16-A SOLAR X-RAY MONITCR NSSDC ID- SRD-118-05

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OGTER INVESTIGATOR) P1 - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTCN, DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO COMPLETE SETS OF IONIZATION-C AMBER AND ELECTROMETER-AMPLIFIER COMBINATIONS. THE IONIZATION CHAMBERS WILL BE SENSITIVE TO SOLAR X-RAYS IN THE 8- TO 16-A RANGE. THE TWO SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES, ALTHOUGH ONLY CNE SET WILL BE SELECTED FOR TELEMETRY TRANSMISSION. DATA WILL BE TRANSMITTED WITH A 30-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIERS WILL BE ABLE TO CHANGE CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE DETECTORS CANNOT BE CALIBRATED IN FLIGHT, BUT THE ELECTROMETER-AMPLIFIERS MAY BE CALIERATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR.

************SOLRAC 118, KREPLIN

EXPERIMENT NAME- 44- TO 60-A SOLAR X-RAY MONITOR NSSDC ID- SRD-IIB-06

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC OI - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF TWO COMPLETE SETS OF IONIZATION-CHAMEER AND ELECTROMETER-AMPLIFIER COMBINATIONS. THE IONIZATION CHAMBERS WILL BE SENSITIVE TO SOLAR X RAYS IN THE 44- TO 60-A RANGE. THE TWO SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES. ALTHOUGH ONLY ONE SET WILL BE SELECTED FOR TELEMETRY TRANSMISSION. DATA WILL BE TRANSMITTED WITH A 30-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIERS WILL BE ABLE TO CHANGE CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE ELECTROMETER-AMPLIFIERS MAY BE CALIBRATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR. THE DETECTORS CAN BE CALIBRATED IN FLIGHT BY COMMANDING A SHUTTER-MOUNTED RADIOACTIVE SOURCE INTO POSITION.

************SOLRAD 118, KREPLIN

EXPERIMENT NAME- 170- TO 1050-A SOLAR EUV MONITOR NSSDC ID- SRD-118-07

LAST REPORTED STATE- PRELAUNCH

1058 EXPERIMENT PERSONNEL (PI=PRINCIPAL INVEST'IGATOR, OI=CTiER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC OI - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTGN, DC 01 - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON. DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF THREE SETS OF LITHIUM FLUORIDE PHOTOSENSITIVE SURFACE DETECTORS COUPLED TO FOUR-RANGE ELECTROMETER-AMPLIFIERS. THE THREE SETS WILL NOT BE REDUNDANT DUE TO THE DIFFERENT FILTERS BEING USED. A BERYLLIUM FILTER WILL LIMIT ONE DETECTOR'S RESPONSE TO THE RANGE FROM 170 TO 500 A. A TIN FILTER WILL LIMIT A SECOND DETECTOR'S RESPONSE TO THE RANGE FROM 450 TO 850 A. AN INDIUM FILTER WILL LIMIT A THIRD DETECTORiS RESPONSE TO THE RANGE FRCM 725 TO 1050 A. THE DETECTOR-ELECTROMETER SETS WILL BE DRIVEN BY SEPARATE POWER SUPPLIES. EACH DETECTOR WILL EE READ EVERY 7.5 SEC. THE ELECTROMETERS MAY BE CALIBRATED DURING FLIGHT WITHOUT DETACHING THE DETECTOR, ALTHOUGH THE DETECTORS CANNOT BE CALIBRATED IN FLIGHT.

***********SOLRAD 118, KREPLIN

EXPERIMENT NAME- 1080- TO 1350-A SOLAR UV MONITOR NSSDC ID- SRD-IIB-OE

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - R.w. KREPLIN NAVAL RESEARCH LAB WASHINGTON, DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF ONE 4-RANGE ELECTROMETER-AMPLIFIER AND THREE IONIZATION CHAMBERS. TWO OF THE IONIZATION CHAMBERS WILL BE THE STANDARD GAS-FILLED CHAMBERS FLOWN ON PREVIOUS SOLRAD SATELLITES. THESE DETECTORS, ELECTRONICALLY AND MECHANICALLY PAIRED. WILL BE DESIGNATED DETECTOR 'A'. ThE THIRD IONIZATION CHAMBER WILL BE AN EVACUATED CHAMBER WITH A LITHIUM FLUORIDE PHOTOSENSITIVE SURFACE, AND WILL BE DESIGNATED DETECTOR 'B'. NORMALLY, DETECTOR B WILL BE CONTINUOUSLY SELECTED FOR TELEMETRY TRANSMISSION AND WILL BE REPLACED ONLY OCCASIONALLY BY DETECTOR A FOR CALIBRATING EXPERIMENT 88 AND EXPERIMENT 9. A MECHANICAL SHUTTER, MOVABLE EY COMMAND. WILL S-IELC THE WINDOW OF DETECTOR A FROM THE SUN. THE ELECTROMETER-AMPLIFIER CAN BE CALIBRATED WITHOUT DETACHING THE DETECTOR FRCM THE SYSTEM. DATA WILL BE SAMPLED AT 15-SEC INTERVALS.

************SOLRAC 118, KREPLIN

EXPERIMENT NAME- 0.5- TO 3- A SOLAR X-RAY MONITOR NSSDC ID- SRD-11B-12

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB WASHINGTON. DC DC OI - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON. OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF THREE IONIZATION CHAMBERS CONNECTED IN PARALLEL TO A SINGLE ELECTROMETER-AMPLIFIER. THE IONIZATION CHAMBERS WILL BE

105S SENSITIVE TO SOLAR X RAYS IN THE 0.5- TC 3.0-A RANGE. DATA WILL BE TRANSMITTED WITH A 15-SEC TIME RESOLUTION. THE ELECTRONETER-AMPLIFIER WILL BE ABLE TO CHANGE CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE DETECTORS CANNOT BE CALIERATED IN FLIGHT, BUT THE ELECTROMETE-AMPLIFIERS MAY BE CALIBRATED ON EACH RANGE WITHOUT DETACHING THE DETECTOR.

************SOLRAD 118, KREPLIN

EXPERIMENT NAME- 1- TO 20-A SOLAR X-RAY MONITCR NSSDC ID- SRD-118-13

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. KREPLIN NAVAL RESEARCH LAB MASHINGTON, DC 01 - R.G. TAYLOR NAVAL RESEARCH LAB WASHINGTON, DC OI - D.M. HORAN NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL CONSIST OF AN IONIZATION CHAMBER AND ONE ELECTROMETER-AMPLIFIER. THE IONIZATION CHAMBER WILL BE SENSITIVE TO SOLAR X RAYS IN THE 1- TO 2C-A RANGE. DATA WILL BE TRANSMITTED WITH A 30-SEC TIME RESOLUTION. THE ELECTROMETER-AMPLIFIER WILL BE ABLE TC CHANGE CURRENT RANGES AUTOMATICALLY OR MANUALLY. THE DETECTOR CANNOT BE CALIBRATED IN FLIGHT. BUT THE ELECTROMETEr-AMPLIFIER MAY BE CALIBRATED GN EACH RANGE WITHOUT DETACHING THE DETECTOR.

************SOLRAD 118. MEEKINS

EXPERIMENT NAME- CONTINUUM (8.8 A) AND MAGNESIUM LINE (9.17 A AND 8.42 A) MONITOR NSSDC ID- SRD-11B-03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATCR. OI=CTHER INVESTIGATOR) PI - J.F. MEEKINS NAVAL RESEARCH LAB WASHINGTON* DC

EXPERIMENT BRIEF DESCRIPTION SOLAR X RAYS WILL BE OBSERVED IN THE MAGNESIUM 11 AND 12 LINES (9.17 AND 8.42 A) AND IN THE CONTINUUM AT 8.8 A. THREE SHA CRYSTALS FIXED AT THREE DIFFERENT ANGLES WILL ALLCW SOLAR X RAYS TO UNDERGO FIRST-ORDER BRAGG REFLECTION INTO THREE PROPORTIONAL COUNTERS. SHOULD THE SPACECRAFT SPIN AXIS BECOME IMPROPERLY ORIENTED, THE SPECTROMETER WOULD FUNCTICN PROPERLY IF THE ASPECT ANGLE WERE NC MORE THAN ONE DEG OFF NOMINAL, ALTHOUGH THE INSTRUMENT WILL THEN FUNCTION AS A SCANNING SPECTRCMETER WITH AN EXTREMELY SMALL SPECTRAL RANGE IN THE VICINITY OF THE TARGET WAVELENGTHS. DATA WILL BE ACCUMULATED OVER INCREMENTS OF 1/64 OF A SPACECRAFT SPIN PERIOD, AND THE EXPERIMENT WILL HAVE A SAMPLING CYCLE OF APPROXIMATELY 1-MIN DURATION.

***********SOLPAD11B, MEEKINS

EXPERIMENT NAME- BRAGG X-RAY POLARIMETER NSSDC ID- SRD-11B-11

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR)

1060 LAB WASHINGTON. DC PI - J.F. MEEKINS NAVAL RESEARCH

EXPERIMENT BRIEF DESCRIPTION CRYSTAL FIXED AT AN THIS EPERIMENT WILL UTILIZE A LITHIUM FLUORIDE FIRST-RDER ANGLE SO AS TO ALLOW SOLAR X-RAYS OF ABCUT 2.8 A TO UNDERGO THE REFLECTION OF BRAGG REFLECTION INTO A PROPORATIONAL COUNTER. SINCE THE ELECTRIC VECTOR OF POLARIZED RADIATION DEPENDS UPON THE ANGLE BETWEEN THE SPIN OF THE THE RADIATION AND THE REFLECTING ANGLE CF THE CRYSTAL. POLARIZED RADIATION. DATA SATELLITE WILL MODULATE THE INTENSITY OF REFLECTED WILL BE PULSES ASSOCIATED wITH 45-DEG SECTORS IN THE ROLL DIRECTION SIGNAL VARIATIONS FRCM ELECTRONICALLY GATED INTO CORRESPONDING ACCUMULATORS. RADIATION. DATA FCR SECTOR TO SECTOR WILL INDICATE THE PRESENCE OF POLARIZED OF SPINS AND EACH 45-DEG SECTOR WILL BE ACCUMULATED FOR AN INTEGRAL NUMBER READ OUT ONCE IN EACH 2-MIN TELEMETRY CYCLE.

**,***#*****SOLRAD 118, SMATHERS

EXPERIMENT NAME- X-RAY MONITOR (0.1-1.6 At C.5-3 A, 1-4 A) NSSDC ID- SRD-118-02

LAST REPORTED STATE- PRELAUNCH

INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER WASHINGTON. DC PI - HoH. SMATHERS NAVAL RESEARCH LAB

EXPERIMENT BRIEF DESCRIPTION MEASURE X-RAY FOUR GAS-FILLED PROPORTIONAL COUNTERS WILL BE USED TO FOUR DETECTORS WILL EMISSION BETWEEN 4 AND 100 KEV IN FOUR CHANNELS. ALL OR BERYLLIUM MOUNTED HAVE 10-MIL BERYLLIUM WINDOWS, PLUS ADDITIONAL ALUMINUM ONCE EVERY 7.5 SEC, IN FRONT OF THE DETECTORS. EACH DETECTOR WILL BE SAMPLED ONLY ONE OR TWO DETECTORS. ALTHOUGH AN OPTIONAL MODE WILL TRANSMIT DATA FROM OF THAT DETECTOR. EFFECTIVELY QUADRUPLING OR DOUBLING THE SAMPLING RATE A RADIOACTIVE SOURCE WHICh IN-FLIGHT CALIBRATION WILL EE PERFORMED BY USING CAN BE MOVED IN FRONT OF THE DETECTORS UPON COMMAND.

************SOLRAC 118. VAMPOLA

EXPERIMENT NAME- SCLAR FLARE ELECTRONS NSSDC ID- SRO-11B-22

LAST REPORTED STATE- PRELAUNCH

OI=CTHER INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. CORP EL SEGUNDO* CA PI - A.L- VAMPOLA AEROSPACE EL SEGUNDC, CA 01 - J.B. BLAKE AEROSPACE CORP LAB WASHINGTON. DC OI - R.W- KREPLIN NAVAL RESEARCH

EXPERIMENT BRIEF DESCRIPTION MAGNETS THIS EXPERIMENT WILL MEASURE SOLAR ELECTRONS. TWO PERMANENT ARRAYS OF SILICON WILL BE USED TO MOMENTUN-ANALYZE INCIDENT ELECTRONS. 12 ENERGY CHANNELS FROM 11 KEV TO DETECTORS WILL COUNT INCIDENT ELECTRONS IN ONCE EVERY 2 MIN. EXCEPT 1.5 MEV. SPIN-INTEGRATED DATA WILL BE OBTAINED CUADRANTS. AND 60-KEV AND THAT 11-KEV AND 405-KEV DATA WILL BE SECTORED INTO WILL BE OBTAINED WITH 15-SEC RESOLUTION. 6 10-KEV DATA +***********SOLRAD 118. WELLER, JR.

1061 EXPERIMENT NAME- GECCORCNAL-EXTRATERRESTRIAL EUV - DETECTOR 1 NSSOC ID- SRD-11B-1

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - C.S. WELLER, JR- NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A COLLIMATED CHANNELTRON PHOTOMULTIPLIER MOUNTED BEHIND A FILTER WHEEL WILL BE USED TC MEASURE EUV RADIATION FROM NON-SOLAR SOURCES. THE FILTER WHEEL WILL ENABLE INVESTIGATORS TO ISOLATE VARIOUS EMISSION LINES BETWEEN 200 AND 1400 A AND ALLOW IN-FLIGHT CALIBRATION THROUGH THE USE OF A RADIOACTIVE SOURCE. THE DETECTOR WILL EE MOUNTED TC LOOK 90 DEG OFF THE SPIN AXIS OF THE SPACECRAFT AND WILL SWEEP THE CELESTIAL SPHERE IN ABOUT 6 MONTHS. EACH DATA SAMPLE WILL BE ACCUMULATED OVER INCREMENTS OF 1/64 OF THE SPACECRAFT'S SPIN* WITH THE SAMPLE SOURCE REFERENCED TO EITHER A STAR PULSE OR THE EARTH PULSE. TFE DATA WILL BE READ OUT IN 2-MIN INTERVALS. THIS EXPERIMENT IS NCT EXPECTED TO BE OPERATED MORE THAN 1 HR PER DAY.

************SOLPAD Ii, WELLER, JR.

EXPERIMENT NAME- GEGCORCNAL-EXTRATERRESTRIAL EUV - DETECTOR 2 NSSDC ID- SRD-118-1

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - C.S. WELLER, JR. NAVAL RESEARCH LAB WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION A COLLIMATED CHANNELTRON PHOTOMULTIPLIER MOUNTED BEHIND A FILTER WHEEL WILL BE USED TO MEASURE EUV RADIATION FROM NON-SOLAR SOURCES. THE FILTER WHEEL WILL ENABLE INVESTIGATORS TO ISOLATE VARIOUS EMISSION LINES BETWEEN 200 AND 1400 A AND ALLOW IN-FLIGHT CALIERATION THROUGH THE USE OF A RADIOACTIVE SOURCE. THE DETECTOR WILL EE MOUNTED TC LOOK 90 DEG OFF THE SPIN AXIS OF THE SPACECRAFT AND WILL SWEEP THE CELESTIAL SPHERE IN ABOUT 6 MONTHS. EACH DATA SAMPLE WILL BE ACCUMULATED OVER INCREMENTS OF 1/64 OF THE SPACECRAFT'S SPIN, WITH THE SAMPLE SOURCE REFERENCED TO EITHER A STAR PULSE OR THE EARTH PULSE. THE DATA WILL BE READ OUT IN 2-MIN INTERVALS. THIS EXPERIMENT IS NOT EXPECTED TO BE OPERATED MORE THAN 1 HR PER DAY.

*****4***4******9**44 a***~******** * SACEL** ** * ** * 8*

SPACECRAFT COMMON NAME- SPACELAE ALTERNATE NAMES- NSSDC ID- SPACLAB

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 00/00/79 SPACECRAFT WEIGHT IN ORBIT- 30000. KG

LAUNCH SITE- CAPE KENNEDY* UNITED STATES LAUNCH VEHICLE- SHUTTLE

SPONSORING COUNTRY/AGENCY INTERNATIONAL ESRO

1062 PLANNED ORBIT PARAMETERS MIN ORBIT TYPE- GEOCENTRIC ORBIT PERIOD- KM ALT INCLINATION- DEG APOAPSIS- KM ALT PERIAPSIS--

PS=PROJECT SCIENTIST) SPACECRAFT PERSONNEL (FM=PROJECT MANAGER, PM - UNKNOWN UNKNOWN

SPACECRAFT SPACELABBRIEF DESCRIPTION WILL CONSIST OF MANNABLE PRESSURIZED LABORATORY MODULES AND SUITABLE FOR CONDUCTING UNPRESSURIZED INSTRUMENT PLATFORMS (PALLETS) SPACE SHUTTLE (NASA) SORTIE MISSIONS. RESEARCH AND APPLICATION ACTIVITIES ON OR TOGETHER, WILL BE THE MODULE AND THE PALLET. EITHER SEPARATELY IN THE SPACE SHUTTLE ORBITER PAYLOAD BAY TRANSPORTED TO AND FROM EARTH ORBIT BY, THE ORBITER THROUGHOUT EACH AND WILL REMAIN ATTACHED TO, AND SUPPORTED AN OPERATICNAL LIFETIME OF 50 MISSION. SPACELPE WILL BE DESIGNED FOR GROUND REFURBISHMENT. NON-ASTRONAUT MISSIONS. EACH OF 7 DAYS DURATION AFTER SIZE WILL BE FOUR SCIENTISTS IN SCIENTISTS AND ENGINEERS (AVERAGE CREW THE SPACE SHUTTLE) WILL BE ON THE ADDITION TO THE TWO CREWMEN OPERATING AND BRING BACK THEIR DATA. THE FLIGHT TO CONTROL EXPERIMENTS AND SUBSYSTEMS ASCENT AND DESCENT AND WILL SPACELAB CREW WILL RIDE IN THE ORBITER DURING AND PERSONAL HYGIENE. SPACELAB USE THESE FACILITIES FOR EATING. SLEEPING, THE FIRST TIME IN SPACE WORK) OF WILL BE THE WORKING BASE* AND THE USE (FOR MEAN THAT THE SPACELAB CREW WILL A SEA-LEVEL OXYGEN/NITROGEN ATMOSPHERE WILL FOR ZERO-G) IN THEIR LABORATORY. SEE HAVE AN EARTH-TYPE ENVIRONMENT (EXCEPT INFORMATION. ESRO/ELDO BULLETIN, AUGUST 1973, FOR FURTI-ER

****** * ****TD IA1A ****4*4******4***** *****

SPACECRAFT COMMON NAME- TO IA ALTERNATE NAMES- PL-721E9 TO 1, 0587; NSSDC ID- 72-014A

NCRMALLY AT A SUBSTANDARD LAST REPORTED STATE- LAUNCHED AND OPERATING DATA ACQUISITION RATE SINCE 02/14/73.

IN ORBIT- 472. KG LAUNCH DATE- 03/12/72 SPACECRAFT WEIGHT

LAUNCH VEHICLE- TA DELTA LAUNCH SITE- VANDENDERG AFB, UNITED STATES

SPONSORING COUNTRY/AGENCY INTERNATIONAL ESRO

INITIAL ORBIT PARAMETERS ORBIT PERIOD- 95.291 MIN EPOCH DATE- 03/12/72 ORBIT TYPE- GEOCENTRIC KM ALT INCLINATION- 97.555 DEG APOAPSIS- 541.9 KM ALT PERIAPSIS- 523.43

RECENT ORBIT PARAMETERS ORBIT PERIOD- 95.141 MIN EPOCH DATE- 09/05/73 ORBIT TYPE- GEOCENTRIC KM ALT INCLINATION- 97.564 DEG APOAPSIS- 535.90 KM ALT PERIAPSIS- 529.19

SCIENTIST) SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, FS=PROJECT

SPACECRAFT BRIEF DESCRIPTION BOXES. THE UPPER THE TD-i SPACECRAFT WAS ESSENTIALLY COMPOSED OF TWO THE SPACECRAFT BOX CONTAINED THE EXPERIMENTS AND THE LOWER BOX CONTAINED TWO LARGE TELESCOPES EQUIPMENT. THE EXPERIMENT COMPARTMENT WAS BUILT AROUND WAS SOLAR (26 AND 30 CM IN DIAM) AND A SPARK CHAMBER. THE SPACECRAFT ATTITUDE CONTROLLED TO POWERED. AND DURING THE SUNLIT PHASE OF ITS ORBIT WAS

1063 ABOUT 1 MIN OF ARC. ONE AXIS WAS POINTED TO WITHIN ONE ARC-MIN CF THE SUN, AND ANOTHER AXIS LAY WITHIN 0.5 DEG OF THE PLANE OF THE SUN* EARTH, AND SPACECRAFT (I.E., THE SPACECRAFT Z AXIS ALWAYS POINTED TOWARDS THE EARTH). BOTH TAPE RECORDERS FAILED WITHIN TWO MONTHS OF LAUNCH, CAUSING DATA RECOVERY TO DROP FROM 95 PERCENT TO LESS THAN 25 PERCENT. IN OCTOBER 1972. THE SPACECRAFT WAS PLACED IN HIBERNATION FOR ABOUT FOUR MONTHS SINCE IT COULD NOT WITHSTAND. FOR ANY LENGTH, PERIODS OF SPACECRAFT NIGHT WHILE IN ACTIVE USE. IN FEBRUARY 1973 THE SPACECRAFT WAS SUCCESSFULLY REACTIVATED AND REAL-TIME TELEMETRY COVERAGE WAS INCREASED TO ABOUT 70 PERCENT. THE COSMIC X-RAY SPECTROMETER EXPERIMENT (S-77) CAUSED ABNORMAL READOUTS IN THE HOUSEKEEPING TELEMETRY CHANNELS. AND HENCE WAS NOT OPERATED UNTIL JULY, 1973.

************TD 1As MONFILS

EXPERIMENT NAME- STELLAR UV RADIATION EXPERIMENT NSSDC ID- 72-014A-01

LAST REPORTED STATE- LAUNCHED AND OPERATING NCRMALLY AT A SUBSTANDARD DATA ACQUISITION RATE SINCE 02/14/73.

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI A.G. - MONFILS U OF LIEGE' LIEGE. BELGIUM PI - R. WILSON U COLLEGE, LONDON LONDON. ENGLAND OI - C. JAMAR U OF LIEGE LIEGE, BELGIUM OI - P.J. BARKER RUTHEFORD HI ENRG. LAB CHILTON* DIDCOT, BERKSHIRE. ENGLAND

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT CONSISTED OF A 1.4-M TELESCOPE WITH A SPECTROMETER BOX ATTACHED TO IT. AN OFF-AXIS PARABOLOID MIRROR (F/3.5s DIAM 275 WM) REFLECTED STARLIGHT ONTO A SYSTEM OF TWO SLITS SITUATED IN THE PRIME FOCAL PLANE. ONE OF THE TWO SLITS FEC THE STELLAR LIGHT INTO A SINGLE PHOTCMETRIC CHANNEL WITH A FILTER LIMITING THE PASSBAND TO 400 A CENTERED AT 2750 A. THE OTHER SLIT WAS MUCH WIDER (11.9 X 17 ARC-MIN), AND LED INTO THE THREE-CHANNEL GRATING SPECTROMETER. ONCE PER ORBIT. THE TELESCOPE, ALIGNED ALONG THE Z AXIS, SCANNED A GREAT CIRCLE OF THE SKY. BECAUSE OF THIS MOTION ACROSS THE SKY, THE PRIMARY IMAGE OF A CERTAIN STAR ENTERING THE TELESCOPE*S FIELD OF VIEW MOVED ACROSS THE PHOTOMETER AND SPECTROPHOTOMETER SLOTS. WHILE THE STAR IMAGE TRAVERSED THE WIDE SPECTROPHOTOMETER SLOT* ITS CORRESPONDING SPECTRUM MOVED IN THE FCCAL PLANE OF THE SPECTROGRAPH ACROSS THE THREE EXIT SLITS, BEHIND WHICH THERE WERE THREE PULSE-COUNTING PHOTCMULTIPLIERS. BY EMPLOYING THE SCANNING MOTION OF THE SATELLITE, A SPECTRUM SCANNING ACTION WAS ACHIEVED WITHOUT THE NEED FOR MOVING PARTS. THE THREE EXIT SLITS OF THE SPECTROPHOTOMETER WERE FIXED AT THE FOLLOWING WAVELENGTHS -- 1350 TO 1760 A, 1760 TO 2160 A AND 2150 TO 2550 A. THE WAVELENGTH REGION FROM 1350 TO 2550 A WAS FULLY COVERED BY THE THREE CHANNELS IN 3.3 SEC* YIELDING A TOTAL OF ABOUT 60 DATA PCINTS. IN EACH CHANNEL THE SPECTRUM WAS SCANNED AT 19.4-A INTERVALS. THE EFFECTIVE PASSBAND DURING EACH INTEGRATION INTERVAL HAVING A FULL-wIDTH HALF-MAXIMUM OF 35 TO 40 A. JUST BEFORE THE TELESCOPE WAS INTEGRATED INTO THE SATELLITE, THE INSTRUMENT WAS EXTENSIVELY CALIBRATED IN ORDER TO ACHIEVE AN ABSOLUTE PHOTOMETRIC ACCURACY BETWEEN 10 AND 20 PERCENT. A RELATIVE PHOTOMETRIC ACCURACY WITHIN 10 PERCENT AND A WAVELENGTH CALIBRATION ACCURATE TO A FEW ANGSTROMS. THIS EXPERIMENT WAS TO DETECT 20,000 STARS. OF WHICH 6000 SHOULD HAVE GIVEN USEFUL UV SPECTRA. IT WAS ABLE TO MEASURE STARS OF MAGNITUDE 10.5. TWO MAJOR OBJECTIVES WERE THE STUDY OF INTERSTELLAR EXTINCTION AND THE PREPARATION OF A UV STAR CATALOG.

KING-A*****4 LANDER ** 444*

1064 SPACECRAFT COMMON NAME- VIKING-A LANDER ALTERNATE NAMES- VIKNG-A NSSDC ID- VIKG-AL

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 3 OTR 75 SPACECRAFT UEIGHT IN CRBIT- 87. KG

LAUNCH SITE- CAPE KENNEDY, UNITED STATES LAUNCH VEHICLE- LT DELTA

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER, PS=PROJECT SCIENTIST) PM - J.S. MARTIN, JR. NASA-LARC HAMPTON, VA PS - G.A. SOFFEN NASA-LARC HAMPTON. VA

SPACECRAFT BRIEF DESCRIPTION THIS SPACECRAFT WILL BE THE LANDING VEHICLE FOR THE TWO-PART IN SPACECRAFT MISSION. IT WILL SOFT-LAND ON THE MARTIAN SURFACE SOMEWHERE THE LATITUDE RANGE PLUS OR MINUS 30 DEG (PREDETERMINED FROM THE ORBITER OF TFE VEHICLE EXPERIMENTS DESIGNED TO CHOOSE A LANDING SPOT). THE LIFETIME LANDER IS DESIGNED TO BE AT LEAST 90 DAYS AFTER LANDING. THE PRIME LANDING AREA WILL BE SELECTED FROM A LOW-ALTITUDE REGION. WITH TWO SECONDARY AREAS ALSO PRESELECTEC IN LOW-ALTITUDE REGIONS. IF THE PRIMARY SITE PROVES TO BE THE UNSATISFACTORY, THE SECONDARY AREAS WILL BE EXAMINED FOR SELECTION. ORBITER WILL HAVE THE CAPABILITY OF BEING MADE SYNCHRONOUS WITH THE LANDER TO PROVIDE FOR DAILY RELAY AND LANDING SITE OBSERVATION FOR 90 DAYS. IT WILL SITES FOR ALSO BE CAPABLE OF OBTAINING DATA FOR THE SELECTION OF LANDING FUTURE MISSIONS. THE LANDER VEHICLE WILL CONTAIN THE MAJORITY OF EXPERIMENTS THE TO BE CONDUCTED ON MARS. THE LANDER WILL HAVE A 70-W POWER CAPACITY. KG (190 LBS.). SCIENTIFIC PAYLOAD FOR THE LANDER WILL WEIGH APPROXIMATELY 87

************VIKING-A LANDER, ANDERSCN

EXPERIMENT NAME- SEISMOLOGY NSSDC ID- VIKG-AL-08

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER.INVESTIGATCR) CA PI - D.L. ANDERSON CAL TECH PASADENA, NA OI - R.F. PRESS MIT CAMBRIDGE. CAMBRIDGE, MA 01 - M.N. TOKSOZ MIT HI OI - G. SUTTON U OF HAWAII HONOLULU. CA OI - R.L. KOVACH STANFORD U STANFORD. TX 01 - G.V. LATHAM U OF TEXAS GALVESTON,

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THE SEISMOLOGY INVESTIGATION WILL BE TO DETERMINE THE SEISMIC BACKGROUND AND EVENT ACTIVITY OF MARS. THREE PERPENDICULAR A FREQUENCY RANGE COMPONENTS OF GROUND MOTION WILL BE MEASURED OVER AS EROAC RESOLUTION AS PRACTICAL (MAXIMUM EMPHASIS OVER THE BAND 0.4 TO 4 HZ). THE 1 HZ. WITH AN WILL BE 50 MILLIMICRONS OR LESS OF GROUND DISPLACEMENT AT TO PLUS OF ACCURACY SUCH THAT TRUE GROUND MOTION AMPLITUDE CAN BE RECOVERED NARROWBAND MINUS 10 PERCENT OR BETTER. DYNAMIC RANGE MAY BE INCREASED BY WILL EE FILTERING OF THE SEISMIC DATA AT THREE FREQUENCIES. THE SEISMOMETER SENSOR MOUNTED IN THE EQUIPMENT AREA OF THE LANDER. THE ORIENTATION OF THE

1065 WILL BE KNOWN TO WITHIN 15 DEG IN AZIMUTH AND 5 DEG IN ELEVATION. TRANSMISSIBILITY OF THE LANDER SHOULD BE GREATER THAN 0.8 FCR FREQUENCIES LESS THAN IC HZ. THE LANDER SHALL HAVE NC RESONANCES LESS THAN 10 HZ WITH 0 GREATER THAN TWO.

************VIKING-A LANDER, BIEMANK

EXPERIMENT NAME- MOLECULAR ANALYSIS NSSDC ID- VIKG-AL-04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - K. BIEMANN MIT CAMBRIDGE, MA 01 - HoC. UREY U OF CALIFCRNIA, SD SAN DIEGC, CA OI - D.M. ANDERSON CRREL HANOVER, NH OI - T. UWEN NEW YORK STATE U STGNYERCOK, NY 01 - J. ORO U OF HOUSTON HOUSTON, 01 - L.E. ORGEL TX SALK INST EICL STUDIES SAN DIEGO. CA OI - G.P. SHULMAN CASA LOMA COLLEGE PACOIMA, CA OI - A.O.C. NIER U OF MINNESOTA MINNEAPCLIS, MN OI - P. TOULMIN, 3RD US GEOLOGICAL SURVEY WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THIS INVESTIGATION IS TO ANALYZE THE MARTIAN FOR ITS SURFACE ORGANIC CONTENT BY VAPORIZING MATERIAL ONTO A GAS CHROMATOGRAPHIC COLUMN WHICH WILL BE CONNECTED TO A FAST-SCANNING (10-SEC) MASS SPECTROMETER. THE FEATING WILL BE ACCONPLISHED IN STEPS TO VAPORIZE THOSE MATERIALS PRESENT WHICH HAVE SUFFICIENT VAPOR PRESSUREs AND ULTIMATELY TO DECOMPOSE PYROLYTICALLY NONVOLATILE SUBSTANCES INTO VOLATILE DEGRADATION PRODUCTS FROM WHICH THE NATURE OF THE MATERIAL CAN THEN BE DEDUCED. TO ACCOMPLISH THE OBJECTIVES OF THIS INVESTIGATION, CERTAIN PRIMARY REQUIREMENTS MUST BE MET. THE SENSITIVITY OF THE MASS SPECTROMETER SHOULD BE SUCH THAT A MASS SPECTRUM TAKEN OF A SINGLE ORGANIC COMPOUND WHICH IS ONE PART IN TEN MILLION (0.1 PPM) SHOWS PEAKS WHICH ARE 1 PERCENT OF THE BASE PEAK. THE MASS RANGE REQUIRED FOR ANALYSIS WILL BE AT LEAST 12 TO 200, WITH UNIT RESOLUTION OR EETTER. THE RELATIVE DYNAMIC RANGE FOR EACH MASS SPECTRUM SHOULD BE 500 TO 1. A CONTROLLED TEMPERATURE WILL BE REQUIRED FOR VAPORIZATION PYROLYSIS UP TO 500 DEG C IN THREE PRESCRIBED STEPS OF 30 SEC. PROVISIONS WILL EE MACE TO ENSURE THAT THE EVOLUTION OF LARGE QUANTITIES OF GAS (AS MUCH AS 10 PERCENT CF SAMPLE WEIGHT) DOES NCT IMPAIR THE FUNCTION OF THE MASS SPECTROMETER. THIS IS TO BE ACCOMPLISHED BY VENTING THE EXCESS GAS BEFORE IT REACHES THE MASS SPECTROMETER. THREE DIFFERENT SAMPLES TAKEN SPECIFIED TIMES AT DURING THE FIRST 60 DAYS OF THE MISSION (COVERING SEASONAL CHANGES) WILL EE STUDIED. THE ORGANIC INVESTIGATION WILL NOT BE INITIATED UNTIL AFTER THE OPERATION OF THE ATMOSPHERIC ANALYSES REQUIRED DURING THE FIRST THREE DAYS.

************VIKING-A LANDER, HARGRAVES

EXPERIMENT NAME- MAGNETIC PROPERTIES NSSDC ID- VIKG-AL-10

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.9. HARGRAVES PRINCETON U PRINCETONs NJ

1066 EXPERIMENT BRIEF DESCRIPTION EXPERIMENTS. THIS EXPERIMENTs WHICH WILL BE PART OF THE LANDER SECTION ON MARS USING WILL MEASURE THE MAGNETIC PROPERTIES OF THE SURFACE PARTICLES IN THE FORM OF THREE MAGNET ARRAYS FOR SAMPLING. DATA RETURNED WILL EE IMAGES OF THE MAGNETIC ARRAYS.

*****O******VIKING-A LANDER, HESS

EXPERIMENT NAME- METEOROLOGY EXPERIMENT NSSDC ID- VIKG-AL-07

LAST REPORTED STATE- PRELAUNCH

INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER TALLAHASSEE, FL PI - S.L. HESS FLORIDA STATE U OI - C.B. LEOVY U CF WASHINGTON SEATTLE* WA 01 - R.M. HENRY NASA-LARC HAMPTON, VA REDONDO BEACH, CA 01 - J.A. RYAN MCDONNELL-DOUGLAS WA OI - J.E. TILLMAN U OF WASHINGTON SEATTLE,

EXPERIMENT BRIEF DESCRIPTION NEAR THE THIS EXPERIMENT WILL MEASURE THE METEOROLOGICAL ENVIRONMENT OF VARIOUS PLANETARY SURFACE AND OBTAIN INFORMATION ABOUT MOTION SYSTEMS AND WIND SCALES. THE ELEMENTS TO BE DETERMINED ARE PRESSURE, TEMPERATURE, OF THE VELOCITY OF THE MARTIAN ATMOSPHERE. DIURNAL AND TEMPORAL VARIATIONS PARAMETERS WILL BE OF PARTICULAR IMPORTANCE. THE SAMPLING RATES AND COMMAND. DURATIONS FUR ANY ONE MARTIAN DAY ARE TO BE SELECTABLE BY GROUND SENSORS ALL MEASUREMENTS ARE TO BE CONTINUED FOR THE LANDER LIFETIME. THE WILL BE MOUNTED ON AN ERECTABLE BOOM.

***********VIKING-A LANDER, KLEIN

EXPERIMENT NAME- BIOLOGY INVESTIGATION NSSDC ID- VIKG-AL-03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) FIELD, CA PI - H.P. KLEIN NASA-ARC MOFFETT CA 01 - J. LEDERBERG STANFORD U STANFOCRD. MA 01 - A. RICH MIT CAMBRIDGE. CA OI - N.H. HOROWITZ CAL TECH PASADENA, FIELD, CA 01 - V.I. OYAMA NASA-ARC MOFFETT MD OI - G.V. LEVIN BIOSPHERICS INC ROCKVILLE,

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL BE COMPOSED OF THREE PARTS. IT WILL MEASURE -- THE (I) THE PHOTOSYNTHETIC AND RESPIRATORY FIXATION CF CARBON DIOXIDE, (2) CHANGES IN GAS COMPOSITION AOOVE A SURFACE SAMPLE IN CONTACT WITH A LIQUID MEDIUM. AND (3) THE CARBON DIOXIDE RELEASED FROM ADCEC LABELED ORGANIC MARS. COMPOUNDS. IT WILL ATTEMPT TO DETERMINE THE PRESENCE OF LIFE ON

*S**********VIKING-A LANDER, MICHAEL, JR.

EXPERIMENT NAME- RADIO SCIENCE NSSOC ID- VIKG-AL-11

LAST REPORTED STATE- PRELAUNCH

1067 EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - W.H. MICHAEL, JR. NASA-LARC HAMPTON, VA OI - I.I. SHAPIRO MIT CAMBRIDGE, MA 01 - G. FJELDBC NASA-JPL PASADENA, CA OI - J.G. DAVIES U OF MANCHESTER MANCHESTER, ENGLAND OI - G.S. LEVY NASA-JPL PASADENA, CA 01 - D.L. CAIN NASA-JPL PASADENA, CA 01 - M. GROSSI RAYTHEON CORP SUDBURY, MA OI - G.L. TYLER STANFORD, L STAKFCRD. CA

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE THE LANDER-TO-EARTH AND ORBITER-TO-EARTF S-BAND COMMUNICATIONS LINK (INCLUDING RANGE AND RANGE-RATE CAPABILITIES), THE LANDER-TO-OREITER UHF RELAY LINK, THE RADAR ALTIMETER, THE TERMINAL DESCENT LANDING RADAR, AND THE ORBITER-TO-EARTH X-BAND DOWNLINK. THE RESULTING DATA WILL BE USED TO DETERMINE THE MARTIAN GRAVITATIONAL FIELD. AXIS OF ROTATION, EPHEMERIS. FIGURE, ATMOSPHERE, STRUCTURE, IONOSPHERE. ANC SURFACE PROPERTIES. IN ADDITION, THE DATA WILL BE USED TO DETERMINE THE LANDER LOCATION, TO STUDY RELATIVITY. TC STUDY THE INTERPLANETARY MEDIUM, AND, IF CONDITIONS PERMIT* TO STUDY THE SOLAR CORONA.

************VIKING-A LANDER, MUTCH

EXPERIMENT NAME- FACSIMILE CAMERA NSSDC 10- VIKG-AL-06

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - T.A. MUTCH BROWN U PROVIDENCE, RI OI - C. SAGAN CORNELL U ITHACA, NY OI - A.B. BINQER PLANETARY SCIENCE INST TUCSON. AZ OI - E.C. MORRIS US GEOLOGICAL SURVEY FLAGSTAFF9 AZ 01 - A.T. YOUNG TEXAS A+M COLLEGE STATION, TX OI - F.O. HUCK NASA-LARC HAMPTON, VA OI - E.C. LEVINTHAL STANFORD U STANFORD, CA

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THE IMAGING INVESTIGATION FROM THE LANDER WILL BE TO VISUALLY CHARACTERIZE THE LANDING SITE, PROVIDING DATA WITH BIOLOGICAL GEOLOGICAL, ANO METEOROLOGICAL RELEVANCE. TWO CAMERAS WITH A 004-DEG SCANNING RESOLUTION WILL BE REQUIRED. THE VERTICAL FIELD OF VIEW FOR EACH CAMERA WILL BE 20 DEG, WITH A CAPABILITY OF OBTAINING A COMPLETE 0- TO 360-DEG HORIZONTAL PANORAMA. VERTICAL POINTING BY COMMAND FOR ANGULAR COVERAGE FROM 40 DEG ABOVE TO 60 DEG BELOW THE HORIZONTAL PLANE OF THE LANDER IN 10-DEG INCREMENTS WILL BE REQUIRED. AZIMUTH POINTING BY COMMAND WILL BE IN 2.5-DEG INCREMENTS. THE CAMERAS WILL BE MOUNTED AT LEAST 1.3 M ABOVE THE MARTIAN SURFACE AND MUST BE CAPABLE OF VIEWING TWO FOOTPADS AND AT LEAST 90 PERCENT OF THE AREA ACCESSIBLE TC THE SURFACE SAMPLER. EACH CAMERA MUST BE CAPABLE OF OBTAINING VISUAL COLOR IMAGERY. PROVISION HAS BEEN MADE TO OPERATE IN ADDITIONAL IR SPECTRAL BANDS BETWEEN 0.8 AND 1.1 MICRONS. HORIZONTAL STEREO WITH A MINIMUM BASE OF 0.8 M WILL BE REQUIRED.

***********VIKING-A LANDER, NIER

EXPERIMENT NAME- ENTRY-ATMOSPHERIC STRUCTURE NSSDC 1D-- VIKG-AL-02

1068 LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) MN PI - A.O.C. NIER U OF MINNESOTA MINNEAPOLIS, MA OI - M.B. MCELROY HARVARD U CAMBRIDGE, TX OI - W.B. HANSON . U OF TEXAS DALLAS, MD OI - N.W. SPENCER NASA-GSFC GREENBELT, FIELD, CA 01 - A. SEIFF NASA-ARC MOFFETT

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT IS DESIGNED TO DETERMINE THE. FRESSURE, TEMPERATURE, ATMOSPHERE THROUGH AND DENSITY VARIATIONS WITH ALTITUDE IN THE LOWER MARTIAN THE ACCELEROMETER CF MEASUREMENT OF ACCELERATION. PRESSURE. ANC TEMPERATURE. STRUCTURE THE GUIDANCE ANC CONTROL SYSTEM WILL BE USED FOR THE ATMOSPHERIC INVESTIGATION.

*********#**VIKING-A LANDER, NIER

EXPERIMENT NAME- ENTRY-ATMOSPHERIC COMPOSITION NSSDC ID- VIKG-AL-12

LAST REPORTED STATE- PRELAUNCH

INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER MINNEAPCLIS, MN PI - A.O.C. NIER U OF MINNESOTA GREENBELT, MD 01 - N.Wv SPENCER NASA-GSFC CAMBRIDGE, MA OI - M.B. MCELROY HARVARD U CALLAS, TX UI - W.B. HANSON U OF TEXAS MOFFETT FIELD. CA 01 - A. SEIFF NASA-ARC

EXPERIMENT BRIEF DESCRIPTION TO THE VIKING ENTRY-ATMOSPHERIC COMPOSITION EXPERIMENT IS DESIGNED SPECIES) NEEDED PROVIDE THE COMPOSITION DATA (FOR BOTH NEUTRAL ANC CHARGED ATMOSPHERE. TO DEFINE THE PRESENT PHYSICAL AND CHEMICAL STATE OF THE MARTIAN MOUNTED A DOUBLE-FOCUSING (ELECTROSTATIC AND MAGNETIC) MASS SPECTROMETER, OPEN ION SOURCE IN AN OPENING IN THE AEROSHELL WITH ITS ELECTRON IMPACT TC MEASURE THE RECESSED BELOW THE SURFACE OF TtE AEROSHELL, WILL BE USED RATIOS CONCENTRATIONS CF THE ATMOSPHERIC SPECIES THAT HAVE MASS-TO-CHARGE ACCURATE FROM I TO 49. IT IS PLANNED THAT THE EXPERIMENT %ILL OBTAIN BCTH ATOMIC AND ALTITUDE PROFILES OF ALL SPECIES, .AND IN PARTICULAR FOR -TWO COLLECTORS WILL MOLECULAR OXYGEN, CARBCON MONOXIDE, AND CARBON DIOXIDE. THE OTHER BE USED -- ONE COVERING THE MASS RANGE FROM I TO 7 AMU AND MASS SPECTRA WILL BE SIMULTANEOUSLY COVERING THE RANGE FROM 7 TO 49 AMU. THE DEFLECTION VOLTAGE OBTAINED BY SWEEPING THE ION ACCELERATION VOLTAGE AND BE APPROXIMATELY ACROSS THE ELECTROSTATIC PLATES. THE SWEEP PERIOD WILL WITHIN EACH SPECTRUM. FIVE SEC, AND A DYNAMIC RANGE OF IE5 WILL BE PROVIDED VACUUM AND OPENED AFTER CALIBRATION, THE INSTRUMENT WILL BE SEALED UNDER ENTRY, THE LANDER WILL WHEN THE LANDER IS RELEASED FROM THE ORBITER. DURING VELOCITY VECTOR, BE TRAVELING WITH ITS AXIS ORIENTED ESSENTIALLY ALONG THE TO THE ENTRANCE PLANE. SO THE AMBIENT SPECIES WILL ENTER AT AN ANGLE NORMAL IONOSPHERIC PROPERTIES A RETARDING POTENTIAL ANALYZER (RPA) WILL MEASURE THE SPECTROMETER. ITS OVER APPROXIMATELY THE SAME ALTITUDE RANGE AS THE MASS GRID IS NEARLY FRONT END WILL MATE TO THE AEROSHELL SO THAT THE ENTRANCE THE REGION OF THE RFA FLUSH TO THE SURFACE, WHICH WILL BE MADE CONDUCTING IN AND COLLECTOR TO PROVIDE A GROUND PLANE. THE SPACE BETWEEN THE ENTRANCE WILL DETERMINE WILL BE ELECTRICALLY SEGMENTED BY FIVE GRIDS WHOSE POTENTIALS REACH THE COLLECTOR. THE ENERGY AND SIGN OF THE CHARGED PARTICLES THAT CAN BE GROUNDED TO THE THE FIRST (ENTRANCE GRID), SECOND, AND LAST GRID WILL

1069 SPACECRAFT. THE THIRD AND FOURTH GRIDS TCGETHER WILL COMPRISE THE RETARDING GRID, AND THE FIFTH GRID. THE SUPRESSOR GRID, WILL eE HELD AT A FIXED POTENTIAL OPPOSITE IN SIGN TO THAT ON THE RETARDING GRID. THREE DIFFERENT LINEAR VOLTAGE RAMPS WILL BE APPLIED IN SUCCESSION TO THE RETARDING GRID. ONE RAMP WILL CCVER THE VOLTAGE RANGE FROM - 75 TO C V(IN ABOUT 1 SEC). USED TO MEASURE SOLAR WIND ELECTRONS AND IONCSPHERIC PHCTOELECTRONS. ANOTHER WILL COVER FROM -1.5 TO 0 V (IN ABOUT ONE SEC), AND MEASURE ELECTRON TEMPERATURES IN THE IONOSPHERE. THE LAST RAMP WILL COVER FROM +15 TO 0 V (IN ABOUT 2 SEC). AND PROVIDE ION TEMPERATURES ANC ION CONCENTRATION DATA. WHEN THE LANDER IS ALIGNED WITH ITS AXIS ALONG THE VELOCITY VECTOR, LOW-ENERGY PLASMA WILL ENTER THE RPA AT AN ANGLE NEARLY NORMAL TO THE APERTURE GRID. EACH PARAMETER WILL BE EVALUATED APPROXIMATELY EVERY 4 KM IN ALTITUDE, A SMALL DISTANCE COMPARED TO THE ANTICIPATED SCALE HEIGHTS. MORE EXPERIMENT DETAIL CAN BE FOUND IN 'ENTRY SCIENCE EXPERIMENT FCR VIKING 1975,' BY A. O. C. NIER. ET AL.. ICARUS. VOL. 16. PP. 74, 1972.

************VIKING-A LANDER, SHORTHILL

EXPERIMENT NAME- PFYSICAL PROPERTIES INVESTIGATION NSSDC ID- VIKG-AL-91

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. SHORTHILL U OF UTAH SALT LAKE CITY, UT 01 - N.W. SPENCER NASA-GSFC GREENeELT, MO OI - R.E. HUTTON TRW SYSTEMS GROUP REDONDO BEACH, CA OI - H.J. MOORE, 2ND U S GEOLOGICAL SURVEY MENLO PARK, CA OI - R.F. SCOTT CAL TECH PASADENA, CA

EXPERIMENT BRIEF DESCRIPTION THE PURPCSE OF THE PHYSICAL PROPERTIES EXPERIMENT INVESTIGATION WILL BE TO DETERMINE THE PHYSICAL PROPERTIES OF THE MARTIAN SURFACE AND ENVIRONMENT AT THE LANDING SITE, PRIMARILY USING ENGINEERING MEASUREMENTS AND SCIENTIFIC INSTRUMENTS REQUIRED TO MEET OTHER MISSION OBJECTIVES. IN PARTICULAR, IT WILL ATTEMPT TO DETERMINE SUCH PROPERTIES AS BULK DENSITY, dEARING STRENGTH, ANGLE OF REPOSE, COHESIGN, ANGLE CF INTERNAL FRICTION, PARTICLE CHARACTERISTICS, THERMAL PARAMETERS, EOLIAN TRANSPORTABILITY, TOPOGRAPHY. AND CERTAIN ENVIRONMENTAL PROPERTIES SUCH AS WIND, TEMPERATURE, AND SOLAR FLUX LEVELS. MAXIMUM USE WILL BE MADE OF HARDWARE AND INSTRUMENTS INTENDED FOR OTHER APPLICATIONS, SUCH AS THE MECHANICAL SUBSYSTEMS AND LANDER CAMERAS. ONLY PASSIVE DEVICES. SUCH AS MIRRORS AND LANDING LEG STROKE GAUGES, ARE BEING ADDED FOR THIS EXPERIMENT.

************VIKINC-A LANDER. TOULMIN. III

EXPERIMENT NAME- X-RAY FLOURESCENCE SPECTROMETER NSSDC ID- VIKG-AL-13

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - P. TOULMIN. III US GEOLOGICAL SURVEY WASHINGTON, DC 01 - A.K. BAIRD POMONA COLLEGE CLAREMONT. CA 01 K. - KEIL U NEW MEXICO ALEUGUERQUE, NM OI - H.J. ROSE US GEOLOGICAL SURVEY WASHINGTON, DC OI B.C. - CLARK MARTIN MARIETTA AERO DENVER. CO

1070 EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE AN ENERGY-DISPERSIVE X-RAY FLUORESCENCE SPECTROMETER IN WHICH FOUR SEALED AND GAS-FILLED PROPORTIONAL COUNTERS WILL DETECT X RAYS EMITTED FROM SAMPLES OF THE MARTIAN SURFACE MATERIALS IRRADIATED BY X RAYS FROM RADIOISOTOPE SOURCES (IRON-55 AND CADMIUM-109). THE OUTPUT OF THE PROPORTIONAL COUNTERS WILL BE SUBJECTED TO PULSEHEIGHT ANALYSIS BY AN ONBOARD STEP-SCANNING SINGLE-CHANNEL ANALYZER WITH ADJUSTABLE COUNTING PERIODS. THIS INSTRUMENT WILL BE LOCATED INSIDE THE LANDER BODY* AND SAMPLES WILL BE DELIVERED TO IT BY THE LANDER SURFACE SAMPLER. CALIBRATION STANDARDS WILL BE AN INTEGRAL PART OF THE INSTRUMENT. RECONSTRUCTED SPECTRA ARE EXPECTED TO YIELD SURFACE COMPOSITION WITH ACCURACIES RANGING FROM A FEW TENS OF PARTS PER MILLION FOR TRACE ELEMENTS TO A FEW PERCENT FOR MAJOR ELEMENTS, DEPENDING UPON THE ELEMENT IN QUESTION.

#*++#****s********#**$***#****8*************#vIKING-A ORBITER ************

SPACECRAFT COMMON NAME- VIKING-A ORBITER ALTERNATE NAMES- PL-733A, VIKNG-A NSSDC ID- VIKG-A

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 3 QTR 75 SPACECRAFT WEIGHT IN CRBIT- 3216. KG

LAUNCH SITE- CAPE KENNEDY* UNITED STATES LAUNCH VEHICLE- TITAN-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- MARSCENTRIC ORBIT PERIOD- 1476. MIN APOAPSIS- 32500. KM ALT PERIAPSIS- 1500. KM ALT INCLINATION- 23. DEG

SPACECRAFT PERSONNEL (PM=PROJECT MANAGER. PS=PROJECT SCIENTIST) PM - J.S. MARTIN, JR. NASA-LARC HAMPTON, VA PS - G.A. SOFFEN NASA-LARC HAPPTON, VA

SPACECRAFT BRIEF DESCRIPTION THE VIKING SPACECRAFT WILL CONSIST OF AN ORBITER AND A LANDER. THE ORBITER WILL BE CAPABLE OF ORBITING THE PLANET MARS IN A HIGH-ECCENTRICITY ELLIPTICAL ORBIT. A LANDER WILL SEPARATE FROM THE ORBITER. ENTER THE MARTIAN ATMOSPHERE, AND SOFT-LAND ON THE SURFACE. ORBITAL, ENTRY, AND SCIENTIFIC DATA FROM THE LANDER WILL BE COLLECTED AND TRANSMITTED TO EARTH. THE SPACECRAFT WILL BE A SOLAR-CELL-POWERED SATELLITE STABILIZED IN 3 AXES, USING INERTIAL AND CELESTIAL REFERENCES. BOTH THE ORBITER AND THE LANDER WILLIHAVE A 90-DAY LIFE EXPECTANCY. THERE WILL BE 500-W POWER CAPACITY FOR THE ORBITER AND A 70-W CAPACITY FOR THE LANDER. SCIENTIFIC AND PHOTOGRAPHIC ANALYSIS INSTRUMENTS WILL WEIGH APPROXIMATELY 77 KG (170 LB).

************VIKING-A ORBITER, CARR

EXPERIMENT NAME- OREITER IMAGING NSSDC ID- VIKG-A -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - M.H. CARP US GEOLOGICAL SURVEY MENLO PARK, CA

1071 01 - W.A. BAUM LOWELL OBSERVATORY FLAGSTAFF, AZ DI - H. MASURSKY US GEOLOGICAL SURVEY FLAGSTAFF, AZ 01 - D.U. WISE U OF MASSACHUSETTS AMHERST, MA OI - G.A. BRIGGS NASA-JPL PASADENA. CA OI - J.A. CUTTS NASA-JPL PASADENA, CA

EXPERIMENT BRIEF DESCRIPTION THE PURPOSES OF THE VIKING ORBITER TV IMAGING EXPERIMENT INVESTIGATICN ARE TO AID IN THE SELECTION OF LANDING SITES FOR THE VIKING LANDERS AND FUTURE MISSIONS, TO MONITOR THE REGION SURROUNDING THE LANDER, AND TO STUDY THE DYNAMIC CHARACTERISTICS OF MARS. THE GEOMETRIC RESCLUTICON OF THE ORBITER IMAGING SYSTEM WILL BE 40 M PER LINE OR BETTER AT A REFERENCE ALTITUDE OF 1500 KM. WITH IMAGE SMEARING FRCM ORBITER MOTION TO BE LESS THAN 50 PERCENT OF THIS RESOLUTION. PRIOR TO LANDER SEPARATION, THE ORBITER WILL BE REQUIRED TO PHOTOGRAPH WITH CONTIGUOUS PICTURES A SWATH AT LEAST 40 KM CROSS-TRACK EY 500 KM DOWN-TRACK ON A SINGLE ORBITAL PASS FROM THE NEAR-PERIAPSIS PORTION OF THE ORBIT. THE NEAR-PERIAPSIS COVERAGE REQUIREMENT AFTER LANDER SEPARATION WILL OBTAIN COMPLETE COVERAGE WITH CONTIGUOUS PICTURES OF AN AREA AT LEAST 50 KM IN RADIUS CENTERED ON THE LANDER. TO OBTAIN BOTH BROAD AREA AND HIGH RESOLUTION COVERAGE, IT WILL BE REQUIRED THAT IMAGERY BE OBTAINABLE FROM THE PERIAPSIS AND APOAPSIS REGIONS CF THE ORBIT USING THE SAME IMAGING SYSTEM. THE DYNAMIC RANGE WILL BE 80 TO 1I AND THE SENSITIVITY WILL BE SUFFICIENT TO OBTAIN PICTURES AS CLOSE TC THE TERMINATOR AS 30 DEG WITH OPTIMUM IMAGE QUALITY AND AS CLOSE AS 5 DEG TO THE TERMINATOR WITH DEGRADEC IMAGE QUALITY.

************VIKING-A ORBITER, FARMER

EXPERIMENT NAME- IR SPECTROMETER -- WATER VAPCR MAPPING NSSDC ID- VIKG-A -03

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - C.B. FARMER NASA-JPL PASADENA* CA 01 - D.D. LAPORTE SANTA BARBARA RSCH CEN GCLETA, CA O1 - D.W. DAVIES NASA-JPL PASADENA. CA

EXPERIMENT BRIEF DESCRIPTION THE OBJECTIVES OF THE IR SPECTROMETRY EXPERIMENT WILL BE TO DETERMINE THE SPATIAL AND TEMPORAL DISTRIBUTION OF WATER VAPOR. TO AID IN THE SELECTION OF LANDING SITES FOR THE VIKING LANDERS, AND (FOR FUTURE MISSIONS) TO MONITOR THE REGION SURROUNDING THE LANDER AND STUDY THE DYNAMIC CHARACTERISTICS OF MARS. THE INFRARED SPECTROMETER WILL BE BORESIGHTED WITH THE IMAGING SYSTEM. IT WILL BE OPERABLE FROM THE PERIAPSIS AND APOAPSIS REGIONS OF THE ORBIT. THE WATER VAPOR MEASUREMENT RANGE WILL BE FROM 1 TO 1000 MICRONS OF PRECIPITABLE WATER WITH AN ACCURACY OF 1 MICRON BETWEEN 1 AND 20 MICRONS AND 5 PERCENT BETWEEN 20 AND 1000 MICRONS. THE INSTANTANEOUS FIELD OF VIEW OF THE INSTRUMENT IS 2 BY 16 MILLIRADIANS.

************VIKING-A ORBITER, KIEFFER

EXPERIMENT NAME- IR RADIOMETRY -- THERMAL MAPPING NSSDC ID- VIKG-A -02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=GTHER INVESTIGATOR)

.1072 LOS ANGELES* CA PI - H.H. KIEFFER U OF CALIFCRNIA9 LA CA OI - G. MUNCH CAL TECH PASADENA, PASADENA, CA OI - E.D. MINER NASA-JPL CA I01- G. NEUGEBAUER CAL TECH PASADENA* GOLETA, CA OI - S. CHASE SANTA BARBARA RSCH CEN

EXPERIMENT BRIEF DESCRIPTION WILL BE TO OBTAIN THE OBJECTIVES OF THE INFRARED RADIOMETRY EXPERIMENT AID IN THE SELECTION SURFACE AND ATMCSPHERIC TEMPERATURE DATA FOR MARS. TO MISSIONS) TO OF LANDING SITES FOR THE VIKING LANDERS, AND (FOR FUTURE THE DYNAMIC MONITOR THE REGIONS SURROUNDING THE LANDER AND STUDY BE BORESIGHTED WITH CHARACTERISTICS OF MARS. THE INFRARED RADIOMETER WILL BE OPERABLE FROM THE THE IMAGING SYSTEM ON THE SCAN PLATFORM AND WILL 28 DETECTORS IN PERIAPSIS AND APOAPSIS REGIONS OF THE ORBIT. A TOTAL OF AND THE INTEGRAL FOUR TELESCOPES WILL COVER FIVE INFRARED WAVELENGTH BANDS 1 DEG K AT 200 DEG K. SOLAR SPECTRUM. THE TEMPERATURE RESOLUTICN WILL BE K. THERE WILL BE AND THE MEASUREMENT RANGE WILL BE FROM 140 TO 330 DEG EACH FIVE SEVEN SIMULTANEOUS FIELDS OF VIEW ARRANGED IN A 'V' PATTERN. MILLIRADIANS IN DIAMETER.

#KN***GB**t** VIKING- LANDER *

SPACECRAFT COMMON NAME- VIKING-B LANDER ALTERNATE NAMES- VIKNG-B NSSDC ID- VIKG-BL

LAST REPORTED STATE- AN APPROVED MISSION

IN ORBIT- 87. KG PLANNED LAUNCH DATE- 3 OTR 75 SPACECRAFT WEIGHT

LAUNCH VEHICLE- LT DELTA LAUNCH SITE- CAPE KENNEDY* UNITED STATES

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

SCIENTIST) SPACECRAFT PERSONNEL (PM=PROJECT MANAGER FPS=PROJECT HAMPTON, VA PM - J.S. MARTIN, JR. NASA-LARC HAMPTON, VA PS - G.A. SOFFEN NASA-LARC

SPACECRAFT BRIEF DESCRIFTION TWO-PART THIS SPACECRAFT WILL BE THE LANDING VEHICLE FOR THE MARTIAN SURFACE SOMEWHERE SPACECRAFT MISSION. IT WILL SOFT-LAND ON THE SITE FCR THIS SECOND WITHIN 30 DEG OF THE MARTIAN EQUATOR. THE LANDING GAINED FROM THE FIRST MISSION (VIKNG-E) WILL BE SELECTED BASED ON KNOWLEDGE AND FROM ORBITAL LANDER'S OPERATION DURING ENTRY AND ON THE SURFACE ORBITER (VIKING-A-LANDER) CR RECONNAISANCE DATA OBTAINED EITHER BY THE FIRST ON ARRIVAL AND SEPARATION. THE SECOND ORBITER (VIKING-B-ORBITER) DEPENDING WILL NOT BE INTERRUPTED IF THE FIRST ORBITER IS USED THE RELAY CPERATION SECOND LANDER WILL BE PRIOR TO ABOUT THE 20TH DAY ON THE SURFACE. THE AS A BACKUP. THE LANDER CAPABLE OF ACCOMPLISHING THE FIRST LANDER MISSION TO BE CONDUCTED ON WILL CARRY THE MAJORITY OF THE SCIENTIFIC EXPERIMENTS A SCIENTIFIC PAYLOAD OF MARS- IT WILL HAVE A 70-W POWER CAPACITY AND APPROXIMATELY 87 KG (190 LBS.).

************VIKING-B LANDER, ANDERSON

EXPERIMENT NAME- SEISMOLOGY NSSDC ID- VIKG-BL-Oe

1073 LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - D.L. ANDERSON CAL TECH PASADENA, CA 01 - F. PRESS MIT CAMBRIDGE, MA 01 - M.N. TOKSOZ MIT CAMBRIDGE, MA 01 - G. SUTTON U OF HAWAII HONOLULU, HI 01 - R.L. KOVACH STANFORD U STANFORD, CA OI - G.V. LATHAM U OF TEXAS GALVESTON, TX

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THE SEISMOLOGY INVESTIGATION WILL BE TO DETERMINE THE SEISMIC BACKGROUNC AND EVENT ACTIVITY OF MARS. THREE PERPENDICULAR COMPONENTS OF GROUND MOTION WILL BE MEASURED OVER AS EROAD A FREQUENCY RANGE AS PRACTICAL (MAXIMUM EMPHASIS OVER THE BAND 0.4 TO 4 HZ). THE RESOLUTION WILL BE 50 MILLIMICRONS OR LESS OF GROUND DISPLACEMENT AT 1 HZ. WITH AN ACCURACY SUCH THAT TRUE GROUND MOTION AMPLITUDE CAN BE RECOVERED TO PLUS OR MINUS 10 PERCENT OR BETTER. DYNAMIC RANGE MAY BE INCREASED BY NARROWBAND FILTERING OF THE SEISMIC DATA AT THREE FREQUENCIES. THE SEISMOMETER WILL EE MOUNTED IN THE EQUIPMENT AREA OF THE LANDER. THE ORIENTATION OF THE SENSOR WILL BE KNOWN TC WITHIN 15 DEG IN AZIMUTH AND 5 DEG IN ELEVATION. TRANSMISSIBILITY OF THE LANDER SHOULD BE GREATER THAN 0.8 FCR FREQUENCIES LESS THAN 1n HZ. THE LANDER SHALL HAVE NO RESONANCES LESS THAN 10 HZ WITH 0 GREATER THAN TWO.

************VIKING-B LANDER, BIEMANN

EXPERIMENT NAME- MOLECULAR ANALYSIS NSSOC ID- VIKG-BL-04

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=OTHER INVESTIGATOR) PI - K. BIEMANN MIT CAMBRIDGE, MA 01 - H.C. UREY U OF CALIFCRNIA, SD SAN DIEGO, CA 01 - D.M. ANDERSON CRREL HANOVER, NH 01 - T. OWEN NEW YORK STATE U STONYBSROK, NY 01 - J. ORO U OF HOUSTON HOUSTON. TX OI - L.E. ORGEL SALK INST BIOL STUDIES SAN DIEGO. CA OI - G.P. SHULMAN CASA LOMA COLLEGE PACOIMA, CA OI - A.D.C. NEIR U OF MINNESOTA MINNEAPCLIS. MN 01 - P. TOULMIN, 3RC. USGS WASHINGTON, DC

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THIS INVESTIGATION IS TO ANALYZE THE MARTIAN SURFACE FOR ITS ORGANIC CONTENT BY VAPORIZING MATERIAL ONTO A GAS CHROMATOGRAPHIC COLUMN WHICH WILL BE CONNECTED TO A FAST-SCANNING (10-SEC) MASS SPECTROMETER. THE HEATING WILL BE ACCOMPLISHED IN STEPS TO VAPORIZE THOSE MATERIALS PRESENT WHICH HAVE SUFFICIENT VAPOR PRESSURE. AND ULTIMATELY TO DECOMPOSE PYROLYTICALLY NONVOLATILE SUBSTANCES INTO VOLATILE DEGRADATION PRODUCTS FROM WHICH THE NATURE OF THE MATERIAL CAN THEN BE DEDUCED. TO ACCOMPLISH THE OBJECTIVES OF THIS INVESTIGATION. CERTAIN PRIMARY REQUIREMENTS MUST BE MET. THE SENSITIVITY OF THE MASS SPECTROMETER SHOULD BE SUCH THAT A MASS SPECTRUM TAKEN OF A SINGLE ORGANIC COMPOUND WHICH IS ONE PART IN TEN MILLION (0.1 PPM) SHOWS PEAKS WHICH ARE 1 PERCENT OF THE BASE PEAK. THE MASS RANGE REQUIRED FOR ANALYSIS WILL BE AT LEAST 12 TO 200. WITH UNIT RESOLUTION OR BETTER. THE RELATIVE DYNAMIC RANGE FOR EACH MASS SPECTRUM SHOULD BE 500 TO 1. A CONTROLLED TEMPERATURE WILL BE REQUIRED FOR

1074 STEPS OF 30 SEC. PYROLYSIS UP TO 500 CEG C IN THREE PRESCRIBED VAPORIZATION OF LARGE QUANTITIES OF BE MADE TO ENSURE THAT THE EVOLUTION PROVISIONS WILL CF WEIGHT) DOES NCT IMPAIR THE FUNCTION GAS (AS MUCH AS 10 PERCENT CF SAMPLE ACCOMPLISHED EY VENTING THE EXCESS GAS THE MASS SPECTROMETER. THIS IS TO BE THREE DIFFERENT SAMPLES TAKEN AT BEFORE IT REACHES ThE MASS SPECTROMETER. OF THE MISSION (COVERING SEASONAL SPECIFIED TIMES DURING THE FIRST 60 DAYS INVESTIGATION WILL NOT BE INITIATED CHANGES) WILL EE STUDIED. THE ORGANIC ANALYSES REQUIRED DURING THE UNTIL AFTER THE OPERATION OF THE ATMOSPFERIC FIRST THREE DAYS.

************VIKING-B LANDER, HARGRAVES

EXPERIMENT NAME- MAGNETIC PROPERTIES NSSDC ID- VIKG-BL-10

LAST REPORTED STATE- PRELAUNCH

INVESTIGATOR, OI=CTHER INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL U PRINCETON, NJ PI - R.B. HARGRAVES PRINCETON

EXPERIMENT BRIEF DESCRIPTION THE LANDER SECTION EXPERIMENTS, THIS EXPERIMENT, WHICH WILL BE PART OF OF THE SURFACE PARTICLES ON MARS USING WILL MEASURE THE MAGNETIC PROPERTIES WILL EE IN THE FORM OF THREE MAGNET ARRAYS FOR SAMPLING. DATA RETURNED IMAGES OF THE MAGNETIC ARRAYS.

***********#VIKING-B LANDER, HESS

EXPERIMENT NAME- METEOROLOGY EXPERIMENT NSSDC ID- VIKG-BL-07

LAST REPORTED STATE- PRELAUNCH

OI=CThER INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATCR, STATE U TALLAHASSEE, FL PI - S.L. HESS FLORIDA WASHINGTON SEATTLE, WA 01 - C.B. LEOVY U OF HAMPTON9 VA OI - R.M. HENRY NASA-LARC REDONDOC BEACH, CA 01 - J.A. RYAN MCDONNELL-DOGLAS SEATTLE, WA 0I - J.E. TILLMAN U OF WASHINGTON

BRIEF DESCRIPTION EXPERIMENT ENVIRONMENT NEAR THE THIS EXPERIMENT WILL MEASURE THE METEOROLOGICAL ABOUT MOTICN SYSTEMS OF VARIOUS PLANETARY SURFACE AND OBTAIN INFORMATION ARE PRESSURE. TEMPERATURE, AND WIND SCALES. THE ELEMENTS TO BE DETERMINED AND TEMPORAL VARIATIONS OF THE VELOCITY OF THE MARTIAN ATMOSPHERE. DIURNAL THE SAMPLING RATES AND PARAMETERS WILL BE OF PARTICULAR IMPORTANCE. TC BE SELECTABLE BY GRCUND COMMAND. DURATIONS FOR ANY ONE MARTIAN DAY ARE THE LANDER LIFETIME. THE SENSORS ALL MEASUREMENTS ARE TO BE CONTINUED FOR WILL BE MOUNTED ON AN ERECTABLE BOOM.

************VIKING-B LANDER, KLEIN

EXPERIMENT NAME- BIOLOGY INVESTIGATION NSSOC ID- VIKG-EL-03

LAST REPORTED STATE- PRELAUNCH OI=CTHER INVESTIGATOR) EXPERIMENT PERSONNEL (pI=PRINCIPAL INVESTIGATCR,

1075 PI - H.P. KLEIN NASA-ARC MOFFETT FIELD. CA 01 - J. LEDERBERG STANFORD U PALO ALTO, CA 0I - A. RICH MIT CAMBRIDGE, NA UI - N.H. HOROWITZ CAL TECH PASADENA, CA 01 - V.I. OYAMA NASA-ARC MOFFETT FIELD, CA OI - G.V. LEVIN BIOSPHERICS INC RCCKVILLE. MD

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL BE COMPOSED OF THREE PARTS. IT WILL MEASURE -- (1) THE PHOTOSYNTHETIC AND RESPIRATORY FIXATION OF CARBON DIOXIDE. (2) THE CHANGES IN GAS COMPOSITION ABOVE A SURFACE SAMPLE IN CONTACT WITH A LIQUID MEDIUM, AND (3) THE CARBON DIOXIDE RELEASED FROM ADDED LABELED ORGANIC COMPOUNDS. IT WILL ATTEMPT TO DETERMINE THE PRESENCE OF LIFE ON MARS.

************VIKING-8 LANDER, WICHAEL, JR.

EXPERIMENT NAME- RACIO SCIENCE NSSDC ID- VIKG-RL-11

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTFER INVESTIGATOR) Pl - W.H. MICHAEL, JR. NASA-LARC HAMPTON, VA OI - 1.1. SHAPIRC MIT CAMBRIDCE, NA 01 - G. FJELDBO NASA-JPL PASADENA, CA OI J.G. - - DAVIES U OF MANCHESTER MANCHESTER. ENGLAND 01 G.S. - LEVY NASA-JPL PASADENA, CA OI - D.L. CAIN NASA-JPL PASADENA, CA 01 - M.D. GROSSI RAYTHEON CORP SUDBURY, MA 01 - G.L. TYLER STANFORD U STANFORD, CA

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE THE LANDER-TO-EARTH AND ORBITER-TO-EARTH S-BAND COMMUNICATIONS LINK (INCLUDING RANGE AND RANGE-RATE CAPABILITIES), THE LANDER-TO-ORBITER UFF RELAY LINK, THE RADAR ALTIMETER, THE TERMINAL DESCENT LANDING RADAR, AND THE ORBITER-TC-EARTH X-BAND COWNLINK. THE RESULTING DATA WILL DE USED TO DETERMINE THE MARTIAN GRAVITATIONAL AXIS FIELD, OF ROTATION, EPHEMERIS, FIGURE, ATMOSPHERE, STRUCTURE, IONOSPHERE, AND SURFACE PROPERTIES. IN ADDITION. THE DATA WILL BE USED TO DETERMINE THE LANDER LOCATICN, TO STUDY RELATIVITY. TO STUDY THE INTERPLANETARY MEDIUM. AND, IF CONDITICNS PERMIT, TO STUDY THE SOLAR CORONA.

************VIKING-B LANDER, MUTCH

EXPERIMENT NAME- FACSIMILE CAMERA NSSDC ID- VIKG-HL-O0

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - T.A. MUTCH BROWN U PROVIDENCE, RI OI - C. SAGAN CORNELL U ITHACA. NY OI - A.B. BINDER PLANETARY SCIENCE INST TUCSON, AZ OI - E.C. MORRIS US GEOLOGICAL SURVEY FLAGSTAFF, AZ OI - A.T. YOUNG TEXAS A+M COLLEGE STATION, TX OI - F.O. HUCK NASA-LARC HAMPTON. VA OI - E.C. LEVINTHAL STANFORD U STANFORD CA

1076 EXPERIMENT BRIEF DESCRIPTION THE PURPCSE OF THE IMAGING INVESTIGATION FROM THE LANDER WILL BE TO VISUALLY CHARACTERIZE THE LANDING SITE, PROVIDING DATA WITH BIOLOGICAL GEOLOGICAL, ANC METEOROLOGICAL RELEVANCE. TWO CAMERAS WITH A 0.04-DEG SCANNING RESOLUTION WILL BE REQUIRED. THE VERTICAL FIELD CF VIEW FOR EACH CAMERA WILL BE 20 DEG WITH A CAPABILITY OF OBTAINING A COMPLETE 30- TO 60O-DEG HORIZONTAL PANORAMA. VERTICAL POINTING BY COMMAND FOR ANGULAR COVERAGE FROM 40 DEG ABOVE TO 60 DEG BELCW (CUTER EDGE OF FIELD-OF-VIEW) THE HORIZONTAL PLANE OF THE LANDER IN 10-DEG INCREMENTS WILL BE REQUIRED. AZIMUTH POINTING BY COMMAND WILL BE IN 2.5-DEG INCREMENTS. THE CAMERAS WILL BE MOUNTED AT LEAST 1.3 M ABOVE THE MARTIAN SURFACE AND MUST BE CAPABLE OF VIEWING TWO FOOTPADS AND AT LEAST 90 PERCENT OF THE AR.EA ACCESSIBLE TO THE SURFACE SAMPLER. EACH CAMERA MUST BE CAPABLE OF OBTAINING VISUAL COLOR IMAGERY. PROVISION WILL BE MADE TO OPERATE IN ADDITIONAL IR SPECTRAL BANDS BETWEEN 0.8 AND 1.1 MICRONS. HORIZONTAL STEREO WITH A MINIMUM BASE OF 0.8 M WILL BE REQUIREC.

*****t***#*VIKING-B LANDER, NIER

EXPERIMENT NAME- ENTRY-ATMOSPHERIC STRUCTURE NSSDC ID- VIKG-BL-02

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATCR, OI=CTHER INVESTIGATOR) P1 - A.O.C. NIER U OF MINNESOTA MINNEAPOLIS, MN 01 - M.D. MCELROY HARVARD U CAMBRIDGE, MA OI - W.B. HANSON U OF TEXAS DALLAS, TX 01 - N.W. SPENCER NASA-GSFC GREENBELT. Md 01 - A. SEIFF NASA-ARC MOFFETT FIELD, CA

EXPERIMENT BRIEF DESCRIPTION THE PARTICULAR ELEMENTS OF MARTIAN ATMOSPHERIC STRUCTURE TO BE DETERMINED WILL BE PRESSURE, TEMPERATURE. AND DENSITY VARIATIONS WITH ALTITUDE IN THE LOWER MARTIAN ATMOSPHERE. THE MEASUREMENTS TO BE MADE TO DETERMINE THESE ATMOSPHERIC PARAMETERS ARE SPACECRAFT ACCELERATION* PRESSURE, AND TEMPERATURE. THE ACCELEROMETER OF THE GUIDANCE AND CONTROL SYSTEM WILL BE USED FOR THE ATMOSPHERIC STRUCTURE INVESTIGATION.

*$**#*#****#VIKING-8 LANDER. NIER

EXPERIMENT NAME- ENTRY-ATMOSPHERIC COMPOSITION NSSDC ID- VIKG-BL-12

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=OTHER INVESTIGATOR) PI - A.O.C. NIER U OF MINNESOTA MINNEAPOLIS, MN O0 - NW- SPENCER NASA-GSFC GREENEELT, MD 01 - M.B. MCELRCY HARVARD U CAMBRIDGE, MA OI - W.D. HANSON U OF TEXAS DALLAS, TX 01 - A. ' SEIFF NASA-ARC MOFFETT FIELD, CA

EXPERIMENT BRIEF DESCRIPTION THE VIKING ENTRY-ATMOSPHERIC COMPOSITION EXPERIMENT IS DESIGNED TO PROVIDE THE COMPOSITION DATA (FOR BOTH NEUTRAL AND CHARGED SPECIES) NEEDED TO DEFINE THE PRESENT PHYSICAL AND CHEMICAL STATE OF THE MARTIAN ATMOSPHERE. A DOUBLE-FOCUSING (ELECTROSTATIC AND MAGNETIC) MASS SPECTROMETER, MOUNTED IN AN OPENING IN THE AEROSHELL WITH ITS ELECTRON IMPACT "OPEN' ION SOURCE

1077 RECESSED BELOW THE SURFACE OF THE AEROSHELL, WILL BE USED TC MEASURE THE CONCENTRATIONS OF THE ATMOSPHERIC SPECIES THAT HAVE MASS-TO-CHARGE RATIOS FROM I TO 49. IT IS PLANNED THAT THE EXPERIMENT WILL OBTAIN ACCURATE ALTITUDE PROFILES OF ALL SPECIES, SPECIFICALLY FOR BOTH ATOMIC AND MOLECULAROXYGEN, CARBON MONOXIDE, AND CARBON DIOXIDE. TWO COLLECTORS WILL BE USED, ONE FOR THE MASS RANGE FROM 1 TO 7 AMU, AND THE OTHER SIMULTANEOUSLY MEASURING IN THE MASS RANGE FROM 7 TO 49 AMU. MASS SPECTRA WILL BE OBTAINEE BY SWEEPING THE ION ACCELERATION VOLTAGE AND THE DEFLECTION VOLTAGE ACROSS THE ELECTROSTATIC PLATES. THE SWEEP PERIOD WILL BE APPROXIMATELY FIVE SEC, AND A DYNAMIC RANGE OF IE5 POWER WILL BE PROVIDED WITHIN EACH SPECTRUM. A RETARDING POTENTIAL ANALYZER (RPA) WILL MEASURE THE IONOSPHERIC PROPERTIES OVER APPROXIMATELY THE SAME ALTITUDE RANGE AS THE MASS SPECTROMETER. ITS FRONT END WILL MATE TO THE AEROSHELL SO THAT THE ENTRANCE GRID IS NEARLY FLUSH TO THE SURFACE, WHICH IS MADE CONDUCTING IN THE REGION OF THE RPA TO PROVIDE A GROUND PLANE. THE SPACE BETWEEN THE ENTRANCE GRID ANC COLLECTOR WILL BE ELECTRICALLY SEGMENTED BY FIVE GRIDS WHOSE POTENTIALS WILL DETERMINE THE ENERGY AND SIGN CF THE CHARGED PARTICLES THAT CAN REACH THE COLLECTOR. THREE DIFFERENT LINEAR VOLTAGE RAMPS WILL BE APPLIED IN SUCCESSION TO THE RETARDING GRID* ONE RAMP WILL COVER THE VOLTAGE RANGE FROM -75 V TO 0 V (IN ABOUT 1 SEC), WHICH WILL BE USED TO MEASURE SOLAR WIND ELECTRONS AND IONOSPHERIC PHOTOELECTRGNS. ANOTHER RAMP WILL COVER FROM -1.5 V TO DV (IN ABOUT I SEC), AND MEASURE ELECTRON TEMPERATURES IN THE IONOSPHERE AND THE LAST FROM +IE V TO C V (IN ABOLT 2 SEC). WHICH WILL BE USED TO PROVIDE ION TEMPERATURE AND ION CONCENTRATION DATA, MORE EXPERIMENT DETAILS CAN BE FOUND INs 'ENTRY SCIENCE EXPERIMENT FOR VIKING 1975,* ICARUS, VOL 16. PP. 74-91, 1972. BY A. O. NIER, ET AL*

************VIKING-B LANDER, SHORTHILL

EXPERIMENT NAME- PHYSICAL PROPERTIES INVESTIGATION NSSDC ID- VIKG-BL-O1

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - R.W. SHORTHILL U OF UTAH SALT LAKE CITY. UT 01 - N.W. SPENCER NASA-GSFC GREENBELT, MD 01 - R.E. HUTTON TRW SYSTEMS GROUP REDONDO BEACH, CA OI - H.J. MOORE, 2ND U S GEOLOGICAL SURVEY MENLC PARK, CA OI - R.F. SCOTT CAL TECH PASADENA, CA

EXPERIMENT BRIEF DESCRIPTION THE PURPOSE OF THE PHYSICAL PROPERTIES EXPERIMENT INVESTIGATION WILL BE TO DETERMINE THE PHYSICAL PROPERTIES OF THE MARTIAN SURFACE AND ENVIRONMENT AT THE LANDING SITE, PRIMARILY USING ENGINEERING MEASUREMENTS AND SCIENTIFIC INSTRUMENTS REQUIRED TO MEET OTHER MISSION OBJECTIVES. IN PARTICULAR, IT WILL ATTEMPT TO DETERMINE SUCH FROPERTIES AS BULK DENSITY, BEARING STRENGTH, ANGLE OF REPOSE, COHESION. ANGLE OF INTERNAL FRICTION, PARTICLE CHARACTERISTICS, THERMAL PARAMETERS, EOLIAN TRANSPORTABILITY. TOPOGRAPHY, AND CERTAIN ENVIRONMENTAL PROPERTIES SUCH AS WINO. TEMPERATURE, AND SOLAR FLUX LEVELS. MAXIMUM USE WILL BE MADE OF HARDWARE AND INSTRUMENTS INTENDED FOR OTHER APPLICATIONS, SUCH AS THE MECHANICAL SUBSYSTEMS AND LANDER CAMERAS. ONLY PASSIVE DEVICES* SUCH AS MIRRORS AND LANDING LEG STROKE GAUGES, ARE BEING ADDED FOR THIS EXPERIMENT.

************VIKING-8 LANDER, TOULMIN, III

EXPERIMENT NAME- X-RAY FLOURESCENCE SPECTROMETER

107B NSSDC ID- VIKG-BL-13

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATOR) PI - P. TOULMIN. III US GEOLOGICAL SURVEY WASHINGTON. DC 01 - A.K. BAIRD POMONA COLLEGE CLAREMCOT, CA OI - K. KEIL U NEW MEXICO ALEUQUERGUE. NM 01 - H.J. ROSE US GEOLOGICAL SURVEY WASHINGTON, DC 01 - B.C. CLARK MARTIN MARIETTA AERO DENVER, CO

EXPERIMENT BRIEF DESCRIPTION THIS EXPERIMENT WILL UTILIZE AN ENERGY-DISPERSIVE X-RAY FLUORESCENCE SPECTROMETER IN WHICH FOUR SEALED AND GAS-FILLED PROPORTIONAL COUNTERS WILL DETECT X RAYS EMITTED FROM SAMPLES OF THE MARTIAN SURFACE MATERIALS IRRADIATED BY X RAYS FROM RADIOISOTOPE SOURCES (IRON-55 AND CADMIUM-109). THE OUTPUT OF THE PROPORTIONAL COUNTERS WILL BE SUBJECTED TO PULSEHEIGHT ANALYSIS BY AN ONBOARD STEP-SCANNING SINGLE-CHANNEL ANALYZER WITH ADJUSTABLE COUNTING PERIODS. THIS INSTRUMENT WILL BE LOCATED INSIDE THE LANDER BODY, AND SAMPLES WILL BE DELIVERED TO IT BY THE LANDER SURFACE SAMPLER. CALIBRATION STANDARDS WILL BE AN INTEGRAL PART OF THE INSTRUMENT. RECONSTRUCTED SPECTRA ARE EXPECTED TO YIELD SURFACE COMPOSITION WITH ACCURACIES RANGING FROM A FEW TENS OF PARTS PER MILLION FOR TRACE ELEMENTS TO A FEW PERCENT FOR MAJOR ELEMENTS. DEPENDING UPON THE ELEMENT IN GUESTION. s4#****+**********#***********4***********+4**VIKING-B ORBITER***********

SPACECRAFT COMMON NAME- VIKING-8 ORBITER ALTERNATE NAMES- PL-733B. VIKNG-B NSSDC ID- VIKG-B

LAST REPORTED STATE- AN APPROVED MISSION

PLANNED LAUNCH DATE- 3 QTR 75 SPACECRAFT WEIGHT IN ORBIT- 3216. KG

LAUNCH SITE- CAPE KENNEDY. UNITED STATES LAUNCH VEHICLE- TITAN-CENT

SPONSORING COUNTRY/AGENCY UNITED STATES NASA-OSS

PLANNED ORBIT PARAMETERS ORBIT TYPE- MARSCENTRIC ORBIT PERIOD- 1476. MIN APOAPSIS- 32500. KM ALT PERIAPSIS- 1500. KM ALT INCLINATION- 23. DEG

SPACECRAFT PERSONNEL (FM=PROJECT MANAGERI PS=PROJECT SCIENTIST) PM - J.S. MARTIN, JR. NASA-LARC HAMPTON. VA

SPACECRAFT BRIEF DESCRIPTION THE VIKING SPACECRAFT WILL CONSIST OF AN ORBITER AND A LANDER. THE ORBITER WILL BE CAPABLE OF ORBITING THE PLANET MARS IN A HIGH-ECCENTRICITY ELLIPTICAL ORBIT. A LANDER WILL SEPARATE FROM THE ORBITER, ENTER THE MARTIAN ATMOSPHERE, AND SOFT-LAND ON THE SURFACE. ORBITAL9 ENTRY. AND SCIENTIFIC DATA FROM THE LANDER WILL BE CCLLECTED AND TRANSMITTED TO EARTH. THE SPACECRAFT WILL BE A SOLAR-CELL-POWERED SATELLITE STABILIZED IN 3 AXES. USING INERTIAL AND CELESTIAL REFERENCES. BOTH THE ORBITER AND THE LANDER WILL HAVE A 90-CAYLIFE EXPECTANCY. THERE WILL BE 500-W POWER CAPACITY FOP THE ORBITER AND A 70-W CAPACITY FOR THE LANDER. SCIENTIFIC AND PHOTOGRAPHIC ANALYSIS INSTRUMENTS WILL WEIGH APPROXIMATELY 77 KG (170 LB).

107( ************VIKING-B ORBITER# CARR

EXPERIMENT NAME- OREITER IMAGING NSSDC ID- VIKG-B -01

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR, OI=CTHER INVESTIGATCR) PI - M.H. CARR US GEOLOGICAL SURVEY MENLO PARK, CA 0I - W.A. BAUM LOWELL OBSERVATCRY FLAGSTAFF. AZ OI - H. MASURSKY US GEOLOGICAL SURVEY FLAGSTAFF, AZ OI - D.U. WISE U OF MASSACHUSETTS AMHERST, MA 01 - G.A. BRIGGS NASA-JPL PASADENA, CA

EXPERIMENT BRIEF DESCRIPTION THE PURPOSES OF THE VIKING ORBITER TV IMAGING EXPERIMENT INVESTIGATICN ARE TO AID IN TtE SELECTION OF LANDING SITES FOR THE VIKING LANDERS AND FO FUTURE MISSIONS, TO MONITOR THE REGION SURROUNDING THE LANDER, AND TO STUDY THE DYNAMIC CHARACTERISTICS OF MARS. THE GEOMETRIC RESOLUTION OF THE ORBITER IMAGING SYSTEM WILL BE 30 METERS PER LINE OR BETTER AT A REFERENCE ALTITUDE OF 1000 KM WITH IMAGE SMEARING FROM ORBITER MOTION TO BE LESS THAN 50 PERCENT OF THIS RESOLUTION. PRIOR TO LANDER SEPARATION. IT WILL BE REQUIRED TO COVER COMPLETELY WITH CONTIGUCUS PICTURES A SWATH AT LEAST 40 KM CROSS-TRACK BY S00 KM DOWN-TRACK ON A SINGLE ORBITAL PASS FROM THE NEAR-PERIAPSIS CF T-E ORBIT. THE NEAR-PERIAPSIS COVERAGE REQUIREMENT AFTER LANDER SEPARATION WILL BE TO OBTAIN COMPLETE COVERAGE WITH CONTIGUOUS PICTURES OF AN AREA AT LEAST 50 KM IN RADIUS, CENTERED ON THE LANDER, ON A SINGLE ORBITAL PASS. THE CAPABILITIES PROVIDED TO ACCOMPLISH THE ABOVE REQUIREMENTS WILL BE UTILIZED TO ACCOMPLISH THE OTHER CITED PURPOSES. TO OBTAIN BOTH BROAD-AREA AND HIGH-RESOLUTION COVERAGE. IT WILL BE REQUIRED THAT IMAGERY BE OBTAINABLE FROM ONE PERISPSIS AND APFOAPSOS REGIONS OF THE ORBIT USING THE SAME IMAGING SYSTEM. THE DYNAMIC RANGE WILL BE 80 TO It AND THE SENSITIVITY WILL BE SUFFICIENT TO OETAIN PICTURES AS CLOSE TO THE TERMINATOR AS 30 DEG WITH OPTIMUM IMAGE QUALITY AND AS CLOSE AS 5 DEG TO ONE TERMINATOR WITH DEGRADED IMAGE QUALITY.

************VIKING-B ORBITER, FARMER

EXPERIMENT NAME- IR SPECTROMETER -- WATER VAPOR MAPPING NSSDC ID- VIKG-8 -C3

LAST REPORTED STATE- PRELAUNCH

EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER INVESTIGATOR) PI - C.B. FARMER NASA-JPL PASADENA. CA 0I - D.D. LAPORTE SANTA BARBARA RSCH CEN GOLETA, CA 01 - D.W. DAVIES NASA-JPL PASADENA. CA

EXPERIMENT BRIEF DESCRIPTION THE OBJECTIVES OF THE IR SPECTROMETRY EXPERIMENT WILL BE TO DETERMINE THE SPATIAL AND TEMPORAL DISTRIBUTION OF WATER VAPOR, TO AID IN THE SELECTION OF LANDING SITES FOR THE VIKING LANDERS. ANC (FOR FUTURE MISSIONS) TO MONITOR THE REGION SURROUNDING THE LANDER AND STUDY THE DYNAMIC CHARACTERISTICS OF MARS. THE INFRARED SPECTROMETER WILL BE BORESIGHTED WITH THE IMAGING SYSTEM. IT WILL BE OPERABLE FROM THE PERIAPSIS AND APOAPSIS REGIONS OF THE ORBIT. THE WATER VAPOR MEASUREMENT RANGE WILL BE FROM I TO 1000 MICRON OF PRECIPITABLE WATER WITH AN ACCURACY CF I MICRON BETWEEN 1 AND 20 MICRONS AND 5 PERCENT BETWEEN 20 AND 1000 MICRONS. THE INSTANTANEOUS

1080 FIELD OF VIEW CF THE INSTRUMENT IS 2 BY 16 MILLIRADIANS.

**s*********VIKING-8 ORBITER. KIEFFER

EXPERIMENT NAME- IR RADIOMETRY -- THERMAL MAPPING NSSDC ID- VIKG-B -02

LAST REPORTED STATE- PRELAUNCH

INVESTIGATOR) EXPERIMENT PERSONNEL (PI=PRINCIPAL INVESTIGATOR. OI=CTHER LOS ANGELES, CA PI - H.H. KIEFFER U OF CALIFCRNIA, LA PASADENA, CA 01 - G. MUNCH CAL TECH PASADENA, CA OI - E.D. MINER NASA-JPL PASADENA, CA 01 - G. NEUGEBAUER CAL TECH CA 01 - S. CHASE SANTA BARBARA RSCH CEN GOLETA,

EXPERIMENT BRIEF DESCRIPTION WILL BE TO OBTAIN THE OBJECTIVES OF THE INFRARED RACICMETRY EXPERIMENT AID IN THE SELECTION SURFACE AND ATMOSPHERIC TEMPERATURE DATA FOR MARS, TO MISSIONS) TO OF LANDING SITES FOR THE VIKING LANDERS, AND (FOR FUTURE MONITOR THE REGIONS SURROUNDING THE LANDER AND STUDY THE DYNAMIC BE BCRESIGHTED WITH CHARACTERISTICS OF MARS. THE INFRARED RADIOMETER WILL FROM THE THE IMAGING SYSTEM CN THE SCAN PLATFORM AND WILL EE OPERABLE CF 28 DETECTORS IN PERIAPSIS AND APOAPSIS REGIONS OF THE ORBIT. A TCTAL THE INTEGRAL FOUR TELESCOPES WILL COVER FIVE INFRARED WAVELENGTH BANDS AND K AT 200 DEG Ks SOLAR SPECTRUM. THE TEMPERATURE RESOLUTICN WILL BE I DEG THERE WILL BE AND THE MEASUREMENT RANGE WILL BE FROM 14C TO 330 DEG K. EACH FIVE SEVEN SIMULTANEOUS FIELDS OF VIEW ARRANGED IN A IV' PATTERN. MILLIRADIANS IN DIAMETER.

1081 SECTION 2 - INDEXES

Title Page

2.1 Cumulative Index of Active and Planned Spacecraft and Experiments ...... 1085 2.2 Cumulative Bar Graph Indexes for Electro- magnetic Radiation Experiments ...... 1117

Solar Broadband Electromagnetic Radiation ...... 1119

Astronomical Broadband Electromagnetic Radiation ...... 1120

Spectral Measurements (All Solar, Except OAO-3) ...... 1121

PREH)EDING PAGE BLANK NOT FILMED

1083 Cumulative Index of Active and Planned Spacecraft and Experiments (Spacecraft Alternate Name and Current Status) SECTION 2.1 - CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS

The following pages contain a list of the names of all spacecraft and experiments that were either active or planned as of March 31, 1974. The spacecraft are listed alphabetically by both common and alternate names. The alternate names are printed with a reference to the NSSDC name are spacecraft common name. Next to the NSSDC spacecraft common printed the sponsoring country and agency, launch date, orbit type, NSSDC ID code, and status. The epoch date, status, and data rate of all launched spacecraft and/or experiments are listed under the CURRENT STATE heading. For prelaunch spacecraft entries, only the status will be shown under this heading; there will be no information for prelaunch data rate, for the spacecraft experiments in this column. The status and most part, reflect the values as of March 31, 1974, that became effective as of the date shown in the EPOCH date column. However, a few changes subsequent to this date may appear. An explanation of the terms used in these columns may be found under Definitions in the annual report. The experiments are listed following the associated spacecraft common name and are ordered alphabetically by the principal investigator's experiment (PI's) last name. The experiment name, NSSDC ID code, and status are also given for each experiment. Finally, each name is fol- lowed by a page number, referencing the description of the spacecraft or experiment, in either the original report (page numbers 3 - 355) or in this supplement (page numbers 1003 - 1081).

1085 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

STATE------LAUNCH ------CURRENT DATE ORBIT TYPE * * SPACECRAFT NAME COUNTRY AND AGENCY STATUS DATA PAGE *************** ****** s******' NSSDC 0ID EPOCH t***t************************ MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME

GEOCENTRIC 73-101A 12/16/73 NORMAL STD 147 AE-C UNITED STATES NASA-OSS 12/16/73 73-101A-13 12/16/73 NORMAL STD 155 BARTH NITRIC OXIDE AIRGLOW 73-101A-01 12/16/73 NORMAL STD 148 BRACE ELECTRON TEMPERATURE AND CONCENTRATION 73-101A-11 12/18/73 NORMAL STO 154 BRINTON BENNETT ION-MASS SPECTREMETER 73-101A-02 12/17/73 NORMAL STD 148 CHAMPION ATMOSPHERIC DRAG 73-101A-03 12/16/73 NORMAL STD 149 DOERING PHOTOELECTRON SPECTROMETER 73-101A-04 12/16/73 NORMAL STD 149 HANSON ICN TEMPERATURE 73-101A-14A 12/16/73 NORMAL STO 156 HAYS AIRGLOW PHOTOMETER 73-101A-05 12/16/73 NORMAL STO 149 HEATH SOLAR EUV FILTER PHOTOMETER 73-101A-06 12/16/73 NORMAL STD 150 HINTEREGGER SOLAR EUV SPECTROPHOTOMETER 73-I01A-10 12/16/73 NORMAL STD 153 HOFFMAN MAGNETIC ION-MASS SPECTROMETER 73-101A-12 12/16/73 NORMAL STD 155 HOFFMAN LOW-ENERGY ELECTRONS 73-101A-07 12/16/73 NORMAL STD 150 NIER OPEN SOURCE NEUTRAL MASS SPECTROMETER 73-10lA-15 12/16/73 NORMAL STD 157 RICE COLD CATHODE IUN GAUGE 73-101A-16 12/16/73 NORMAL STO 158 RICE CAPACITANCE MANOMETER 73-1I01A-09 12/16/73 NORMAL STD 152 SPENCER NEUTRAL GAS TEMPERATURE AND CONCENTRATION

GEOCENTRIC AE-D APPROVED 158 AE-D UNITED STATES NASA-OSS MARCH 75 -11 165 SARTH NITRIC OXIDE AIRGLOW AE-D -01 159 BRACE ELECTRON TEMPERATURE AND CONCENTRATION AE-0 -02 160 CHAMPION ATMOSPHERIC DRAG AE-D AE-D -03 160 DOERING PHOTOELECTRON SPECTROMETER -04 160 HANSON ION TEMPERATURE AE-D 167 HAYS AIRGLOW PHOTOMETER AE-D -13 161 HINTEREGGER SOLAR EUV SPECTROPHOTOMETER AE-D -06 164 HOFFMAN ION COMPOSITION AND CONCENTRATION AE-D -10 166 HOFFMAN LOW-ENERGY ELECTRONS AE-D -12 AE-U -C7 162 NIER OPEN SOURCE NEUTRAL MASS SPECTROMETER AE-D -08 163 PELL CLOSED SOURCE NEUTRAL MASS SPECTROMETER AE-D -14 167 RICE CAPACITANCE MANOMETER AE-D -15 168 RICE COLD CATHODE ION GAUGE 164 SPENCER NEUTRAL GAS TEMPERATURE AND AE-D -09 CONCENTRATION

GEOCENTRIC AE-E APPROVED 168 AE-E UNITED STATES NASA-OSS SEPT. 75 169 BRACE ELECTRON TEMPERATURE AND CONCENTRATION AE-E -01 -10 174 BRINTON ICN COMPOSITION AND CONCENTRATION AE-E -02 169 CHAMPION ATMOSPHERIC DRAG AE-E -03 170 DOERING PhOTOELECTRON SPECTROMETER AE-E AE-E -04 170 HANSON ION TEMPERATURE AE-E -11 175 HAYS AIRGLOW PHOTOMETER -05 171 HEATH SOLAR EUV FILTER PHOTOMETER AE-E -06 171 HINTEREGGER SOLAR EUV SPECTROPHOTCMETER AE-E -07 172 NIER OPEN SOURCE NEUTRAL MASS SPECTRCMETER AE-E -08 173 PELZ CLOSED SOURCE NEUTRAL MASS SPECTRCMETER AE-E -12 176 RICE CAPACITANCE MANOMETER AE-E PRECEDING PAGE BLANK NOT FILMED 1087 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * ********s*********************************** ******** ******************************* NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

RICE COLD CATHODE ION GAUGE AE-E -13 177 SPENCER NEUTRAL GAS TEMPERATURE AND AE-E -09 174 CONCENTRATION

AEHOS-d FED. REP. OF GERMANY GFW JULY 74 GEOCENTRIC AEROS-B APPROVED 177 UNITED STATES NASA-OSS KRANKOWSKY MASS SPECTROMETER (MS) AEROS-8-01 NESKE ELECTRON CONCENTRATION 178 IN THE IONOSPHERE AEROS-B-03 179 ROEMER ATMOSPHERIC DRAG ANALYSIS AEROS-D-06 180 SCHMIDTKE FLUX AND SPECTRAL DISTRIBUTION CF SOLAR AEROS-B-04 179 EUV RAD AND THEIR TEMP AND SPATIAL VAR SPENCER NEUTRAL ATMOSPHERE TEMPERATURE AEROS-8-05 179 EXPERIMENT SPENNER ENERGY DISTRIBUTION OF IONS AND AEROS-e-02 178 ELECTRONS

ALPO SEE LUNAR POLAR ORB-DAUGHTER

ALPO SEE LUNAR PCLAR ORE-MOTHER

ALSEP 12 SEE APOLLC 12 LM/ALSEP

ALSEP 14 SEE APOLLO 14 LM/ALSEP

ALSEP 15 SEE APOLLC 15 LM/ALSEP

ALSEP 16 SEE APOLLO 16 LM/ALSEP

ALSEP 17 SEE APOLLO 17 LM/ALSEP

ANS THE NETHERLANDS NIVR AUG. 74 GEOCENTRIC ANS APPROVED 181 UNITED STATES NASA-OSS DE JAGER LOW-ENERGY X-RAY EXPERIMENT ANS -02 182 GURSKY HIGH ANGULAR AND SPECTRAL RESOLUTION ANS -03 182 OBSERVATIONS OF COSMIC X-RAY SOURCES VANDUINEN UV TELESCOPE ANS -01 181 APOLLO 12 LM/ALSEP UNITED STATES NASA-OMSF 11/14/69 LUNAR LANDER 69-099C 11/19/69 NORMAL STD 40 UNITED STATES NASA-OSS FREEMAN SUPRATHERMAL ION DETECTOR 69-099C-05- 03/18/70 NORMAL SUBS 42 LATHAM PASSIVE SEISMIC 69-099C-03 10/00/73 PARTIAL SNYDER SOLAR WINO SPECTROMETER SUBS 41 69-099C-02 11/05/71 PARTIAL STD 41

APOLLO 12C SEE APOLLC 12 LM/ALSEP

APOLLO 14 LM/ALSEP UNITED STATES NASA-OMSF 01/31/71 LUNAR LANDER 71-008C 02/05/71 NORMAL STD 55 UNITED STATES NASA-OSS FREEMAN SUPRATHERMAL ION DETECTCR 71-00C-06 03/29/72 PARTIAL SUBS 57

1088 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENT'S BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH 4 ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * *#t** * **+******************** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

JOHNSON COLD CATHODE ION GAUGE EXPERIMENT 71-008C-07 03/29/72 PARTIAL SUBS 57 KOVACH ACTIVE SEISMIC 71-008C-05 12/07/73 PARTIAL SUBS 56 LATHAM PASSIVE SEISMIC 71-008C-04 11/17/72 PARTIAL SUBS 56 O'BRIEN CHARGED PARTICLE LUNAR ENVIRONMENT 71-008C-08 02/01/73 PARTIAL SUBS 58

APOLLU 14C SEE APOLLC 14 LM/ALSEP

76 APOLLO 15 LM/ALSEP UNITED STATES NASA-OMSF 07/26/71 LUNAR LANDER 71-063C 07/30/71 NORMAL STD UNITED STATES NASA-OSS BATES LUNAR DUST DETECTOR 71-063C-09 07/31/71 NORMAL STD 79 78 FREEMAN SUPRATHERMAL ION DETECTOR 71-063C-05 12/16/71 PARTIAL STD JOHNSON COLD CATHODE ION GAUGE EXPERIMENT 71-063C-07 12/16/71 PARTIAL SUBS 79 STD 78 LANGSETH HEAT FLOW 71-063C-06 08/07/71' PARTIAL 77 LATHAM PASSIVE SEISMIC 71-063C-01 07/31/71 NORMAL STD

APOLLO 15C SEE APOLLC 15 LM/ALSEP

1003 APOLLO 16 LM/ALSEP UNITED STATES NASA-OMSF 04/16/72 LUNAR LANDER 72-031C 04/21/72 NORMAL STD UNITED STATES NASA-OSS 1003 DYAL LUNAR SURFACE MAGNETOMETER 72-031C-03 08/17/73 NORMAL STD SUBS 102 KOVACH ACTIVE SEISMIC 72-031C-02 12/07/73 NORMAL LATHAM PASSIVE SEISMIC 72-031C-01 04/21/72 NORMAL STD 101

APOLLO 16C SEE APOLLO 16 LM/ALSEP

STD 123 APOLLO 17 LM/ALSEP UNITED STATES NASA-OMSF 12/07/72 LUNAR LANDER 72-096C 12/11/72 NORMAL UNITED STATES NASA-GSS STD 124 BERG LUNAR EJECTA AND'METEORITES 72-096C-05 12/17/72 PARTIAL 125 KOVACH LUNAR SEISMIC PROFILING EXPERIMENT 72-096C-06 12/20/72 NORMAL SUBS LANGSETH HEAT FLOW 72-096C-01 12/11/72 NORMAL STD 124 SUBS 126 WEBER LUNAR SURFACE GRAVIMETER 72-096C-09 12/12/72 PARTIAL

APOLLO 17C SEE APOLLO 17 LM/ALSEP

APOLLO-SOYUZ TEST PROJ. SEE ASTP

APPLICATIONS EXP MISSION SEE HCMM

182 ASTP UNITED STATES NASA-OMSF 07/15/75 GEOCENTRIC ASTP APPROVED U.S.S.R. SAS ANG INFLUENCE OF WEIGHTLESSNESS ON THE ASTP -06 184 IMMISCIBILITY OF MONOTECTIC ALLOY SYSTEMS BOWYER EXTREME ULTRAVICLET ASTRONOMY ASTP -01 183 BUWYER HELIUM GLOW ASTP -02 183 BUCKER BIOSTACK ASTP -16 188 187 CRISWELL EFFECTS OF SPACE FLIGHT ON THE CELLULAR ASTP -14 RESPONSE OF MAN DONAHUE ULTRAVIOLET ATMOSPHERIC ABSORPTION ASTP -03 183

1089 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH * -- CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * ***********:::::::* *******************:;******S***$****+************ *PRINC.INVEST.NAME EXPERIMENT NAME **** NSSDC 10 EPOCH STATUS DATA PAGE * MMDDYY RATE NO.

FRIEDMAN SKY-EARTH X-RAY OBSERVATICNS ASTP -04 GATOS 184 DETERMINATION OF ZERO-GRAVITY EFFECTS ON ASTP -08 185 ELECTRONIC MATERIALS PROCESSING HANNING ELECTROPHORESIS ASTP -11 186 LARSON ROLE OF CONVECTION IN SOLIDIFICATION ASTP -07 185 PROCESS MARTIN IN HIGH COERCIVE STRAIGHT MAGNET PCLYMORPHONUCLEAR LEUKOCYTE RESPONSE TO ASTP -13 187 INFECTION REED SURFACE TENSICN INDUCED CCNVECTION IN ASTP -05 184 ENCAPSULATED LIQUID METALS IN ZERO G TAYLOR MICROBIAL EXCHANGE TEST ASTP -15 187 TOBIAS LIGHT FLASHES AND OTHER SENSATIONS FROM ASTP -17 188 COSMIC PARTICLES WEIFFENBACH SPACECRAFT-TO-SPACECRAFT DOPPLER ASTP -12 186 TRACKING WIEDEMEIER CRYSTAL GROWTH FROM THE VAPOR PHASE IN ASTP -09 185 ZERO-GRAVITY ENVIRONMENT YUE ZERO-GRAVITY SOLIDIFICATICN OF NACL-LIF ASTP -10 186 EUTECTIC

ASTP-APOLLO UNITED STATES NASA-OMSF 07/15/75 GEOCENTRIC ASTP-A APPROVED 189 ASTP-SOYUZ U.S.S.R. SAS 07/15/75 GEOCENTRIC ASTP-S APPROVED 189 ASTRO NETHERLAND SAT. SEE ANS

ATMOSPHERE EXPLORER-C SEE AE-C

ATMOSPHERE EXPLORER-D SEE AE-D

ATMOSPHERE EXPLORER-E SEE AE-E

ATS 5 UNITED STATES NASA-OA 08/12/69 GEOCENTRIC DAROSA RADIO BEACON 69-069A 06/01/73 PARTIAL SUBS 37 69-069A-12 08/12/69 NORMAL STD 39 MCILWAIN OMNIDIRECTIONAL HIGH-ENERGY PARTICLE 69-069A-03 08/00/72 NORMAL DETECTOR SUBS 38 MCILWAIN BIDIRECTIONAL LOW-ENERGY FARTICLE 69-069A-11 08/00/73 PARTIAL DETECTOR SUBS 39 SUGIURA MAGNETIC FIELD MONITOR 69-069A-13 06/10/73 PARTIAL SUBS 40 ATS-E SEE ATS 5

ATS-F UNITEC STATES NASA-OA 06/02/74 GEOCENTRIC ATS-F APPROVED 190 ARNOLDY LOW-ENERGY PROTON/ELECTRON EXPERIMENT ATS-F -03 191 BLAKE OPNIDIRECTIONAL SPECTROMETER ATS-F -07 192 COLEMAN, JR. MAGNETOMETER EXPERIMENT ATS-F -02 191 DAVIES RADIO BEACON ATS-F -09 193 FRITZ MEASUREMENT OF LOW-ENERGY PROTONS ATS-F -01 191

1090 AND EXPERIMENTS CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

CURRENT STATE------LAUNCH ------COUNTRY AND AGENCY DATE ORBIT TYPE * SPACECRAFT NAME NSSDC ID EPOCH STATUS DATA PAGE *************************************** *****A***************** * MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME

ATS-F -06 192 MASLEY SOLAR COSMIC FAYS AND GEOMAGNETICALLY TRAPPED RADIATION 192 ATS-F -05 192 MCILWAIN AURCRAL PARTICLES EXPERIMENT ATS-F -08 193 SHENK GEOSYNCHRONOUS VERY HIGH RESCLUTION RADIOMETER (GVHRR) 191 -04 MECHANISMS AND ATS-F WINCKLER PARTICLE ACCELERATION DYNAMICS OF THE OUTER TRAPPING REGION

ORB-DAUGHTER AUTO.LUNAR POLAR OREITER SEE LUNAR POLAR

ORB-MCTHER AUTO.LUNAR POLAR CREITER SEE LUNAR PCLAR

1 BMS SEE ELMS

BMS SEE ELMS 2 APPROVED 194 CNES UNSCHED GEOCENTRIC CAS-B CAS-5 FRANCE UNITED STATES NASA-OSS APPROVED 194 CRC 11/00/74 GEOCENTRIC CAS-C CAS-C CANADA UNITED STATES NASA-OSS

COOPERATIVE APPLICA SAT. SEE CAS-8

COOPERATIVE APPLICA SAT. SEE CAS-C

COPERNICUS SEE OAC 3 PROPOSED 1003 TGKYC U 1975 GEOCENTRIC CORSA CORSA JAPAN CORSA -01 1004 HAYAKAWA COSMIC X-RAY DETECTION (0.25 - 60 KEV) CORSA -02 1005 ODA COSMIC HEAVY PRIMARY PARTICLES APPROVED 196 ESRC I QTR 75 GEOCENTRIC COS-B COS-B INTERNATIONAL

COSMIC RAY SATELLITE SEE CORSA

COSMIC RAY SATELLITE-B SEE CDS-E

DAD SEE DADE-A

DAD SEE DADE-E APPROVED 145 NASA-OSS 2HALF 75 GEOCENTRIC DADE-A DADE-A UNITED STATES OADE-A -01 145 KEATING ATMOSPHERIC DRAG DENSITY 145 MASS DADE-A -02 NIER ATMCSPHERIC CCMFOSITICN SPFCTROMETER APPROVED 146 NASA-GSS 2HALF 75 GEOCENTRIC DADE-B DADE-8 UNITED STATES

1091 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH *--- CURRENT STATE------* SPACECRAFT NAME CCUNTRY AND AGENCY DATE ORBIT TYPE * ** *** ******************************************************** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

KEATING ATMOSPHERIC CRAG DENSITY DADE-B -01 146 NIER ATMOSPHERIC COMPOSITION MASS OADE-B -02 147 SPECTROME TER

DAUGHTER SEE [SEE-F

DIAPU FRANCE 12/00/75 GEOCENTRIC DIAPO PROPOSED 200 DUAL AIR DENSITY EXPL-A SEE DADE-A

DUAL AIR DENSITY EXPL-2 SEE DADE-e

OUAL-A U.S.S.R. 08/00/75 DUAL-A UNKNOWN 201 DUAL-Al U.S.S.R. 08/00/75 DUAL-Al UNKNOWN 202 EARTH RES TECH SAT.-A SEE ERTS 1

EARTH RES TECH SAT.-d SEE ERTS-E

ELMS 1 UNITED STATES DOD-USAF C7/00/75 GEOCENTRIC ELMS 1 APPROVED 1005 ELMS 2 UNITED STATES DOD-USAF 10/00/75 GEOCENTRIC ELMS 2 APPROVED 1005 ERS 26 SEE OV5-6

ERTS 1 UNITED STATES NASA-OA 07/23/72 GEOCENTRIC 72-058A 07/23/72 ARLUSKAS MULTISPECTRAL SCANNER (MSS) NORMAL STD 102 72-058A-02 07/23/72 NORMAL STD 10* PAINTER DATA COLLECTION SYSTEM (OCS) 72-058A-03 WEINSTEIN 07/23/72 NORMAL 5TD 105 RETURN BEAM VIDICON (RBVI CAMERA SYSTEM 72-058A-01 07/23/72 NORMAL STD 103

ERTS-A SEE ERTS 1

ERTS-D UNITED STATES NASA-OA 1 QTR 75 GEOCENTRIC ERTS-B APPROVED 202 ARLUSKAS MULTISPECTRAL SCANNER (MSS) ERTS-B -02 204 PAINTER DATA COLLECTICN SYSTEM (DCS) ERTS-B -03 204 WEINSTEIN RETURN BEAM VIDICON iRBV) CAMERA SYSTEM ERTS-B -01 203

ESGEO SEE ESRC GECS

ESRO 4 INTERNATIONAL ESRC 11/22/72 GEOCENTRIC 72-092A 11/22/72 BOYD POSITIVE ION SPECTROMETER NORMAL STD 119 72-092A-01 11/22/72 NORMAL STO 120 DE JAGER SOUTHERN POLAR CAP SOLAR PARTICLE 72-092A-04 11/22/72 NORMAL SPECTROMETER STD 122 HULTOUIST AUCRAL PARTICLE SPECTRCMETER 72-092A-03 11/22/72 NORMAL LUST NORTHERN POLAR CAP SOLAR PARTICLE STD 121 72-092A-05 11/22/72 NORMAL STO 122 SPECTROMETER VON ZAHN NEUTRAL MASS SPECTROMETER 72-092A-02 11/22/72 NORMAL STD 121

1092 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECFAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

CURRENT STATE------* LAUNCH * ------TYPE * * SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT **********s NSSDC ID EPOCH STATUS DATA PAGE ******************* **********3********** **************** MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME +

ESGEO APPROVED 205 ESRO GEOS INTERNATIONAL ESRO 2 OTR 76 GEOCENTRIC 206 BOYD THERMAL PLASMA FLOW ESGEO -02 206 GEISS LOW-ENERGY IC CCMPOSITIOK ESGEU -03 207 GENORIN ELECTROMAGNETIC WAVE FIELDS ESGEO -06 207 HULTOUIST LOW-ENERGY ELECTRON AND PROTON PITCH ESGEO -04 ANGLE DISTRIELTION 208 MARIANI TRIAXIAL FLUXGATE MAGNETCMETER ESGEO -09 208 MELZNER DC ELECTRIC FIELD AND GRADIENT 8 ESGEO -C8 ELECTRON BEAM CEFLECTICN 208 PETERSEN DC FIELDS ESGEO -07 207 PETIT VLF FIELD ANTENNA ESGEO -05 206 PFOTZER ELECTRON AND PRCTON PITCH ANGLE ESGEO -01 CISTRIBUTION

68-114A 12/15/68 NORMAL STD 22 ESSA 8 UNITED STATES ESSA 12/15/68 GEOCENTRIC 68-114A-01 03/00/69 PARTIAL SUBS 23 NESS STAFF AUTCMATIC PICTURE TRANSMISSION (APT) SYSTEM

EUROPEAN X-RAY OUS SAT. SEE HELOS

EXOS-A APPROVED 209 EXOS-A JAPAN TOKYC U 00/00/77 GEOCENTRIC 209 UNKNOWN IONOSPHERIC PROBES EXOS-A -01 209 UNKNOWN ENERGETIC PARTICLE DETECTCRS EXOS-A -02 210 UNKNOWN X-RAY AND ULTRAVIOLET ALRGRAL TELESCOPES EXOS-A -03 210 UNKNOWN MAGNETOMETER EXOS-A -04

EXOS- APPROVED 210 EXOS-B JAPAN TOKYO U 00/00/78 GEOCENTRIC 211 UNKNOWN MAGNETOSPHERIC PLASMA PROBE EXOS-B -01 211 UNKNOWN ENERGETIC PARTICLE DETECTCRS EXOS-8 -02 211 UNKNOWN ELECTROMAGNETIC FIELD FLUCTUATION EXOS-8 -03 CETECTORS

EXOS-C APPROVED 212 EXOS-C JAPAN TOKYC U 01/00/78 GEOCENTRIC 212 UNKNOWN X-RAY AND GAMMA-RAY ASTRONOMICAL EXOS-C -01 TELESCOPES 212 UNKNOWN ULTRAVIOLET TELESCOPE EXOS-C -02 213 UNKNOWN INFRARED TELESCCPE EXOS-C -03 213 UNKNOWN ENERGETIC PARTICLES EXOS-C -04

EXOSAT SEE HELOS

EXOSPHERIC SAT. A SEE EXOS-A

EXOSPHERIC SAT. e SEE EXOS-E

EXOSPHERIC SAT. C SEE EXOS-C

1093 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

SLAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * & ****t*t********#*******************+ NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

EXPLORER 37 SEE SOLRAD 9

EXPLORER 42 SEE SAS-A

EXPLORER 43 SEE [MP-I

EXPLORER 44 SEE SOLRAD 10

EXPLORER 45 SEE S-CUBED A

EXPLORER 46 SEE METEOROID TECHNGLCGY SAT

EXPLORER 47 SEE IMP-H

EXPLORER 49 SEE RAE-B

EXPLORER 50 SEE IMP-J

EXPLORER 51 SEE AE-C

FR-2B SEE CAS-8

GEODETIC SATELLITE-C SEE GEOS-C

GEOS SEE ESRO GEOS

GEOS-C UNITED STATES NASA-OA UNSCHED. GEOCENTRIC GEOS-C APPROVED 1006 JACKSON C-BANC SYSTEM GEOS-C -03 1007 MINOTT LASER CUBE SYSTEM GECS-C -04 1007 STANLEY RADAR ALTIMETER SYSTEM GEOS-C -01 1008 STECKEL S-RAND TRANSPCNDER SYSTEM GEOS-C -02 1009 UNKNOWN US NAVY DOPPLER SYSTEM GEOS-C -05 1009

GEOSTATION.METEOROL SAT. SEE GMS

GMS JAPAN NASDA 12/00/76 GEOCENTRIC GMS APPROVED 1010 JAPAN JMA

GOES-A SEE SMS-C

GOES-B UNITED STATES DEPTCFCOM 3 OTR 7b GEOCENTRIC GOES-B APPROVED 214 UNITED STATES NASA-CA NESS STAFF VISIBLE-INFRARED SPIN-SCAN RADICMETER GOES-B -01 215 (VISSR) UNKNOWN METEOROLOGICAL CATA CCLLECTION AND GOES-B -05 217 TRANSMISSION SYSTEM WILLIAMS ENERGETIC PARTICLE MONITOR GOES-e -02 216 WILLIAMS SOLAR X-RAY MONITOR GOES-8 -03 216

1094 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRNT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT IYPE * ID EPOCH STATUS DATA PAGE ***t******************************** *********************************************** NSSDC MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME

WILLIAMS MAGNETIC FIELD MONITUO GOES-8 -34 216

APPROVED 217 GOES-C UNITEC STATES DEPTCFCOM 4 OTR 76 GEOCENTRIC GOES-C UNITED STATES NASA-CA NESS STAFF VISIOLE-INFRARC SPIN-SCAN RADICMETER GOES-C -01 218 (VISSR) UNKNOWN METEOROLOGICAL CATA CCLLECTICN AND GOES-C -05 220 TRANSMISSION SYSTEM WILLIAMS ENERGETIC PARTICLE MONITCR GOES-C -C2 219 WILLIAMb SOLAR X-RAY MONITOR GOES-C -03 219 WILLIAMS MAGNETIC FIELD MCNITOR GOES-C -04 219

220 GP-A UNITED STATES NASA-CSS 1975 GRAVR-A APPROVED VESSUT GRAVITATIONAL FCTENTIAL AS A FUNCTION GRAVR-A-31 221 OF TIME

GRAVITATIONAL REDSFIFT P SEE GP-A

GRAVR-A SF GP-A

APPROVED 221 HAWKEYE UNITED STATES NASA-OSS MAY 1974 GEOCENTRIC HAWKEYE FRANK LOA-ENERGY PRCTCNS AND ELECTRONS HAWKEYEC-2 222 GURNETT ELF/VLF RECEIVERS HAWKEYE-03 222 VAN ALLEN TRIAXIAL FLUXGATE MAGNETOETER HAWKEYC-01 222

1010 HCMM UNITEC STATES NASA-CA 03/00/77 GEOCENTRIC AEM-A PROPOSED HOVIS HEAT CAPACITY MISSION RADIOMETER AEM-A -01 1011

1012 HEAO-A UNITED STATES NASA-OSS IHALF 77 GEOCENTRIC HEAD-A APPROVED BOLDT COSMIC X-RAY EXPERIMENT HEAO-A -02 1012 FRIEDMAN LARGE AREA CCSMIC X-RAY SURVEY HEAO-A -01 1013 GURSKY X-RAY SCANNING NCDULATICN CCLLIMATOR mEAO-A -03 1013 PETERSON LOw-ENERGY GAMMA-PAY SKY SURVEY HEAO-A -04 1014

1015 HEAQ-8 UNITED STATES NASA-OSS 2HALF 78 GECCENTRIC HEAO-8 APPROVED BOLOT SCLIO-STATE X-RAY DETECTOR HEAO-B -05 1015 CLARK A CURVED-CPYSIAL DRAGG X-RAY HEAO- -n3 1015 SPFCTROMETER GIACCONI ACNITOR PROPCRTIChAL COLNTER HEAO-8 -11 1016 GIACCONI HIGH RESOLUTICN IMAGER HEAO-O -02 1016 GURSKY IMAGING PROPCRTICNAL CCUNTER HEAO-B -34 1016

HEAD-C UNITEC STATES NASA-OSS 2HALF 79 GEOCENTRIC HEAO-C APPROVED 1017 ISRAEL HEAVY NUCLEII EXPERIMENT HEAO-C -33 1017 JACOdSON GAMMA RAY LINE SPECTRCMETER HEAO-C -01 1018 KOCH ISIOTOPIC COMPCSITION OF COSMIC RAYS HEAO-C -04 1018 MEYER PRIMARY COSMIC RAY ELECTRCNS HEAO-C -C5 1019

1095 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS HY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH * ------CURRENT STATE------S SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * * **** ******************* ******************************* * NSSDC 10 EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

HEAT CAPACTY MAP MISSION SEE HCMM

HELIOCENTRIC SEE ISEE-C

HELLOS-A FEC. REP. OF GERMANY 6BMF 2HALF 74 HELIOCENTRIC HELIO-A APPROVED 223 UNITED STATES NASA-OSS FECHTIG MICRUMETECROIC DETECTOR AND ANALYZER HELIO-A-12 227 GURNETT COARSE FREQUENCY, FINE TIME RESOLUTION HELIO-A-04 224 SPECTRUM ANALYSIS GURNETT FINE FREQUENCY, COARSE TIME RESCLUTION HELIO-A-05 225 SPECTRUM ANALYSIS GURNCTT 5 KHZ-2 MHZ RACIO WAVE HELIO-A-06 225 KEPPLER ENhRGETIC ELECTRCN DETECTCR HELIO--A-10 227 KUNUW COSMIC-RAY PARTICLES HELIO-A-07 226 LtlNERT ZCUIACAL LIGHT FHCTOMETER HELIO-A-l 227 NESS FLJXGATE MAGNETCMETER FCR AVERAGE FIELDS HELIU-A-02 224 NEUBAUER FLUXGATE MAGNETCMETER FUR FIELD HELIO-A-01 223 FLUCTUATIONS NEUaAUER SEARCH COIL MAGNETCMETER HELIO-A-03 224 ROSENOAUER PLASMA DETECTCRS hELIO-A-09 226 TRAINOR GALACTIC AND SOLAR COSMIC RAYS HELIO-A-08 226

HELIOS-B FED. PEP. OF GERMANY BMwF JAN. 76 HELIOCENTRIC HELIO-B APPROVED 228 UNITED STATES NASA-OSS FECHTIG MICROMETEOROID DETECTOR AND ANALYZER HELIO-8-12 233 GURNETT CLARSE FREUUENCY. FINE TIME RESOLUTION HELiO-B-04 230 SPECTRUM ANALYSIS GURNETT FINE FREQUENCY. COARSE TIME RESOLUTION HELIO-8-05 230 SPECTRUM ANALYSIS GURNCTT SO KHZ-2 MHZ RADIO WAVE HELIO-8-06 230 KEPPLER ENERGETIC ELECTRON OETECTCR HELIO--10 232 KUNUW COSMIC-RAY PARTICLES HELIO-0-07 231 LEINERT ZCDIACAL LIGHT PHOTOMETER HELIO-8-I1 232 NESS FLUXGATE MAGNETCMETER FCR AVERAGE FIELDS HELIO-B-02 229 NEUDAUER FLUXGATE MAGNETCMETER FOR FIELD HELIO-8-OI 229 FLLCTUATIONS NEUBAUER SEARCH COIL MAGNETCMETEF HELIO-B-03 229 ROSENGAUER PLASMA DETECTCRE HELIO-0-09 232 TRAINOR GALALTIC AND SOLAR COSMIC RAYS HELIO-O-08 231

HELGS INTERNATIONAL ESRO C8/00/79 GEOCENTRIC HELOS PROPOSED 239 UNKNOWN MEDIUM-ENERGY CCSMIC X-RAY PACKAGE HELOS -01 240 UNKNOWN LOW-ENERGY COSMIC X-RAY PACKAGE HELOS -02 240

HEOS 2 INTERNATIONAL ESRO 01/31/72 GEOCENTRIC 72-005A 01/31/72 NORMAL STD 86 OILWORTH HIGH-ENERGY ELECTRONS 72-OC5A-05 01/31/72 NORMAL STD 88 ELLIGTT FLUXGATE MAGNETOMETER 72-OC5A-01 01/31/72 NORMAL STO 87 FECHTIG MICtfIMETEORIfI C ETECTOR 72-OC5A-07 01/31/72 NORMAL STU 89

1096 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECFAFT AND EXPERIMENTs BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRENT STATE------4 SPACECRAFT NAME CCUNTRY AND AGENCY DATE ORMIT TYPE * EPOCH STATUS DATA PAGE ******** * 4************* ****** ************************************0*t************* NSSOC ID RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY

STD 88 PAGE PARTICLE COUNTER TELESCCPF 72-0C5A-04 01/31/72 NORMAL 88 PETERS SOLAP VLF COSERVATION 72-OC5A-03 01/31/72 NORMAL STD STD 87 PIZZELLP ELECTRON AND FRCTON MEASUREMENTS (2C 72-0CSA-02 01/31/72 NORMAL EV-50 KEV) STO 89 ROSENBAUER SCLAW WIND MEASLREMENTS (23C EV-16 KEV) 72-OCSA-06 01/31/72 NORMAL

HEOS-A2 SEC HFOS 2

HI.ECCEN LUN OCCULT.SAT. SEE HELS

IME-O SEE ISCE-P

IME-H SEE ISLE-C

IME-M SEE ISEE-A

IMP 6 SEE IMP-I

IMP 7 SEE IMP-H

IMP 8 SEE IMP-J

STD 109 IMP-H UNITED STATES NASA-CSS 05/23/72 GEOCENTRIC 72-073A 09/23/72 NORMAL NORMAL STD 113 BAME MCEASUREMENT CF SOLAR PLASMA 72-073A-10 09/23/72 STD 109 BRIUGE MEASUREMENT CF SOLAR PLASMA 72-073A-02 12/11/73 PARTIAL CLINE STUDY OF COSMIC-RAY, SOLAR. AND 72-073A-13 10/13/72 NORMAL STD 115 MAGNETOSPHERIC ELECTRONS STD 110 FRANK MEASUREMENT CF LOW-ENERGY PROTONS AND 72-073A-04 09/23/72 NORMAL ELECTRONS STD 110 GLOECKLER IONS AND ELECTRCNS IN THE ENERGY RANGE 72-073A-03 11/25/72 PARTIAL ,.1 TO 2 MEV STO 112 KRIMIGIS PROPAGATION CHARACTERISTICS CF SOLAR 72-073A-08 12/11/73 PARTIAL PROTONS AND ELECTRONS STD 113 MCOUNALD SCLAR- ANC CCSIC-RAY PARIICLES 72-073A-09 09/26/72 NORMAL STO 115 OGILVIF SOLAR WIND ION CCMPOSITION 72-073A-12 09/24/72 NORMAL SUBS 114 SCARF PLASMA %AVE EXPERIMENT 72-073A-11 09/24/72 NORMAL NORMAL STD 112 SIMPSON SCLAR FLARE HIG-Z//LOw-E AND LOW-Z 72-073A-07 09/23/72 ISCTCPE EXPt-rIMENT NORMAL STD III STONE ELCCTrONS ANI) HYDROGEN ANC HELIUM 72-073A-06 09/23/72 ISOTOPES STD 111 *ILLIAM, NCRGETIC ELECTRONS AND PRCTCNS 72-073A-05 09/26/72 NORMAL

NORMAL STD 59 IMP-I UNIT'C STATES NASA-CSS 13/13/71 GECCENTRIC 71-019A 03/13/71 STO 60 AGGSON rLfECTRfJSTATIC FICLDS 71-019A-02 03/20/71 NORMAL STD 61 ANGERSON ME)IUM-ENFEGY SCLAR PROTCNS AND 71-01SA-06 03/13/71 NORMAL ELECT RONS STD 64 bAME MEASURFEMENT CF SOLAR PLASMA 71-019-11 03/15/71 NORMAL STD 62 tOSTROM MCNITL;RING CF SCLAR P OTONS 71-019A-07 03/14A71 NORMAL

1097 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY ANC AGENCY DATE ORBIT TYPE * **********************Sh***,***************s******************s************ ********* NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

FRANK LCW-ENERGY PRCTCNS ANC ELECTRONS 71-019A-05 03/13/71 NORMAL STD 61 GURNETT ELECTROSTATIC WAVES AND RADIO 71-019A-C3 03/14/71 NORMAL STD 60 NOISE -- IONA GURNETT ELECTROSTATIC hAVES AND RADIO NCISE 71-019A-16 03/13/71 NORMAL STD 66 HADDOCK INTERPLANETARY LONG-WAVELENGTH RADIO 71-019A-13 03/13/71 NORMAL STD 65 ASTRONCMY EXPERIMENT KELLOGG ELECTROSTATIC WAVES AND RADIO NCISE 71-019A-12 03/11/74 PARTIAL STD 65 MCDONALD SOLAR AND GALACTIC COSMIC-RAY STUDIES 71-01A-CB 10/14/71 PARTIAL STD 63 NESS MEASUREMENT OF MAGNETIC FIELDS 71-01gA-01 03/13/71 NORMAL STD 59 SIMPSON NLCLEAR COMPOSITION OF COSMIC AND SCLAR 71-O31A-09 03/13/71 PARTIAL STD 63 PARTICLE RADIATIGNS

IMP-J UNITEC STATES NASA-CSS 10/26/73 GEOCENTRIC 73-078A 10/26/73 NORMAL STD 241 AGGSON ELECTROSTATIC FIELDS 73-078A-11 10/26/73 NORMAL STD 24, BAME MEASUREMENT CF SOLAR PLASMA 73-078A-1G 10/26/73 NORMAL STD 245 BRIDGE MEASUREMENT OF SOLAR PLASMA 73-078A-C2 10/26/73 NORMAL STD 241 FRANK MEASUREMENT OF LOW-ENERGY PRCTONS AND 73-078A-04 10/26/73 NORMAL STD 242 ELECTRONS GLOECKLER SCLID-STATE DETECTORS 73-07eA-03 10/26/73 NORMAL STD 242 GURNETT ELECTROSTATIC WAVES AND RADIO NOISE 73-078A-12 10/26/73 NORMAL STD 246 KRIMIGIS PROPAGATION CHARACTERISTICS CF SOLAR 73-07EA-08 04/00/74 PARTIAL STD 244 PROTONS AND ELECTRONS MCDONALD SCLAR- AND CCSMIC-RAY PARTICLES 73-07EA-09 10/26/73 NORMAL STD 244 NESS MAGNETIC FIELD EXPERIMENTS 73-078A-01 10/26/73 NORMAL STD 241 SIMPSON SCLAR FLARE tIGH-Z/LGW-E AND LOW-Z 73-078A-07 10/26/73 NORMAL STO 244 EXPERIMENTS STONE ELECTRONS AND HYORCGEN ANC HELIUM 73-07EA-06 10C/26/73 NORMAL STD 243 ISOTOPES WILLIAMS ENERGETIC ELECTRCNS AND PPCTCNS 73-07eA-05 IC/26/73 NORMAL STD 243

IMP-K SEE ISEE-A

IMP-K PRIME SEE ISEE-8

INDIAN SCIENTIFIC SAT. INDIA ISAC 12/00/74 GEOCENTRIC INDASAT APPROVED 246 DANIEL SOLAR NEUTRON AND GAMMA PAYS INDASAT-02 247 RA3 X-RAY ASTRONOMY INDASAT-01 247 SATYAPRAKAS- IONOSPHERIC ELECTRON TRAP AND UV INDASAT-03 247 CHAMBERS

INJUN 6 SEE HAWKEYE

INJUN-F SEE HAWKEYE

INT ULTRAVIOLFT EXPL SEE IUE

INTA SATELLITE SEC INTASAT

1098 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS EY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

*LAUNCH * ------CURRENT STATE------4 SPACECRAFT NAME CCUNTRY AND AGENCY DATE ORBIT TYPE PAGE +es#####4********#** ********* NSSOC ID EPOCH STATUS DATA RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY

248 INTASAT SPAIN CNIE-INTA 07/00/75 GEOCENTRIC INTASAT APPROVED UNITED STATES NASA-OSS UNKNOWN CIONOSPHERIC EEACCN INTASAT-01 248

10/30/73 NORMAL UNKN 1019 INTERCOSMOS 10 U.S.S.R. UNKNCCN 10/30/73 GECCENTRIC 73-082A UNKN 1020 UNKNOWN MAGNETIC FIELD MEASUREMENT 73-082A-01 10/30/73 NORMAL NORMAL UNKN 1020 UNKNOWN ELECTRIC FIELC MEASUREMENT 73-082A-02 10/30/73 1040 UNKNOWN LOW-ENERGY PARTICLES 73-082A-03 10/30/73 NORMAL UNKN UNKN 1021 UNKNOWN VLF EMISSIONS 73-082A-04 10/30/73 NORMAL UNKN 1021 UNKNOWN ELECTRON CONCENTRATION AND 73-082A-05 10/30/73 NORMAL TEMPERATURE

IONOSPHERE SOUNDING SAT. SEE ISS

1021 ISEE-A UNITED STATES NASA-OSS 2HALF 77 GEOCENTRIC MOTHER APPROVED INTERNATIONAL ESRO ANDERSON ENERGETIC ELECTRCNS AND PROTONS MOTHER -10 287 BAME 5-EV TO 4C-KEV PROTON ANC 5-EV TC MOTHER -01 282 20-KEV ELECTRON PLASMA PRCBE FRANK HOT PLASMA MOTHER -03 283 GURNETT IC-HZ TO IC-KHZ MAGNETIC AND 10-HZ TO MOTHER -07 285 200-KHZ ELECTRIC FIELD TRIAXIAL PROBES HARVEY ACTIVE PLASMA EXPERIMENT MOTHER -08 1022 HELLIWELL VLF WAVE INJECTION MOTHER -13 288 HEPPNER DC ELECTRIC FIELDS MOTHER -11 287 HOVESTADT LOW-ENERGY CGSMIC-RAY COMPOSITION MOTHER -05 284 MOZER OC TO 12-HZ ELECTRIC FIELD PROBE MOTHER -06 1022 OGILVIE THREE-DIMENSIONAL (SIX AXES), MOTHER -02 283 6-EV TO 10-KEV ELECTRON SPECTROMETER RUSSELL MAGNETIC FIELCS MOTHER -04 284 SHARP PLASMA COMPOSITION MOTHER -12 289 SIMPSON MEDIUM-ENERGY COSMIC RAYS MOTHER -14 288 WILLIAMS ENERGETIC ELECTRONS AND PROTONS MOTHER -09 286

1023 ISEE-B UNITED STATES NASA-CSS 2HALF 77 GEOCENTRIC DAUGHTR APPROVED INTERNATIONAL ESRL ANDERSON ENERGETIC ELECTRONS AND PROTONS DAUGHTR-08 200 EGIDI S-EV TO 25-KEV ION AND 35-EV TO 7-KEV DAUGHTR-02 197 ELECTRON PLASMA PROdES FRANK HOT PLASMA DAUGHTR-03 198 GURNETT 10-HZ TO 10-K-Z MAGNETIC AND 10-HZ TO DAUGHTR-05 199 200-KHZ ELECTRIC FIELD MCNOAXIAL PROBES HARVEY RADIC PROPAGATICON RECEIVER DAUGHTR-06 1024 KEPPLER ENERGETIC ELECTRONS AND PROTONS DAUGHTN-07 199 PASCHMANN 5C-EV TO 40-KEV PROTON ANC 5-EV TO DAUGHTR-01 197 20-KEV ELECTRON PLASMA PROBE RUSSELL MAGNETIC FIELCS DAUGHTR-04 198

199 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

SLAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE 4 **************#**##*~t*e**#* ***** *# *** * ** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

ISEE-C UNITED STATES NASA-CSS ?HALF 78 HELIOCENTRIC HELOCTR APPROVED 233 ANDERSON X RAYS AND ELECTRONS HELOCTR-09 237 BAME 150-EV TO 7-KEV PROTON ANC 5-EV TC HELOCTR-01 234 2.5-KEV ELECTrON PLASMA PROBE DE FEITER ENERGETIC PROTONS HELOCTR-08 237 HECKMAN HIGH-ENERGY COSMIC RAYS HELOCTR-05 236 HOVESTADT LOW-ENERGY COSMIC-RAY CCOMPOSITION HELOCTR-03 235 MEYER COSMIC-RAY ELECTRONS AND NUCLEI HELOCTR-06 236 OGILVIE MASS SPECTROMETER FOR 470 TO 10.500 EV HELOCTR-11 238 PFR CHARGE AND 1 TO 5-5 AMU PER CHARGE SCARF 2C-HZ TO I-KHZ MAGNETIC AND 20-HZ TC HELOCTR-07 237 ICC-KHZ ELECTRIC FIELD DETECTORS SMITH MAGNETIC FIELCS HELOCTR-02 234 STEINBERG 20--KHZ TO 3-MHZ RADIO MAPPING HELOCTR-10 238 STONE COSMIC-RAY COMPCSITION HELOCTR-12 239 VON ROSENVING SOLAR. GALACTIC, AND MAGNETOSPHERIC HELOCTR-04 235 ENERGETIC PARTICLES WILCOX SOLAR AND INTERFLANETAR MAGNETIC FIELDS HELOCTR-13 239 (CORRELATIVE STUDY)

ISIS 1 CANADA CRC 01/30/69 GEOCENTRIC 69-009A 01/30/70 PARTIAL SUBS 24 UNITED STATES NASA-OSS BARRINGTON VLF RECEIVER 69-009A-03 01/30/70 NORMAL SUBS 26 BRACE CYLINDRICAL ELECTROSTATIC PROBE 69-OC9A-07 01/30/70 NORMAL SUBS 27 CALVERT FIXEO FREQUENCY SOUNDER 69-009A-02 01/30/70 NORMAL SUBS 26 FORSYTH RADIO DEACON 69-009A-09 01/30/69 PARTIAL SUBS 29 HAHTZ COSMIC RADIO NOISE 69-009A-10 01/30/70 NORMAL SUBS 29 MCDIARMIO ENERGETIC PARTICLE DETECTORS 69-009A-04 01/30/70 NORMAL SUBS 27 SAGALYN SPHERICAL ELECTROSTATIC ANALYZER 69-009A-08 01/30/70 NORMAL SUBS 28 *HITTEKER SWEEP FREQUENCY SOUNDER 69-009A-01 01/30/70 NORMAL SUBS 25

ISIS 2 CANADA CRC 04/01/71 GEOCENTRIC 71-024A 02/04/73 NORMAL SUBS 66 UNITED STATES NASA-OSS ANGER 3914- TO 5577-A PHOTOMETER 71-024A-11 02/04/73 NORMAL SUBS 72 BARRINGTON VLF RECEIVER 71-024A-03 02/04/73 NORMAL SUBS 68 BRACE CYLINDRICAL ELECTROSTATIC PROBE 71-024A-07 02/04/73 NORMAL SUBS 71 CALVERT FIXED FREQUENCY SOUNDER 71-024A-02 02/04/73 NORMAL SUBS 68 FOHSYTH RADIO BEACON 71-024A-09 04/23/71 PARTIAL SUBS 72 HARTZ COSMIC RADIO NOISE 71-024A-10 02/04/73 NORMAL SUBS 72 HEIKKILA SOFT-PARTICLE SPECTROMETER 71-024A-05 -02/04/72 PARTIAL STD 70 HOFFMAN ION MASS SPECTRCMETER 71-024A-06 02/04/73 NORMAL SUBS 70 MAIER RETARCING POTENTIAL ANALYZER 71-024A-08 02/04/73 NORMAL SUBS 71 MCOIARMID ENERGETIC PARTICLE DETECTCRS 71-024A-04 02/04/72 PARTIAL STD 69 SHEPHERD 6300-A PHOTOMETER 71-024A-12 02/04/73 NORMAL SUBS 73 WHITTEKER SWEEP FREQUENCY SOUNDER 71-024A-01 02/04/73 NORMAL SUBS 67

ISIS-A SEE ISIS 1

1100 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS EY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

*LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * STATUS DATA PAGE ****************** ******* *************** *** **t*++** ************** NSSDC ID EPOCH RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY

ISIS-B SEE ISIS 2

ISS APPROVED 249 ISS JAPAN NASDA 02/00/76 GEOCENTRIC FUGONO ION MASS SPECTROMETER ISS -04 250 MIYAZAKI RETARDING POTENTIAL PRCEE ISS -03 250 249 UNKNOWN SWEEP FREQUENCY SOUNDER ISS -01 UNKNOWN RADIO NOISE ISS -02 250

ITOS-D SEE NOAA 2

ITOS-F SEE NOAA 2

254 ITOS-G UNITED STATES NOAA-NESS JULY 74 GEOCENTRIC ITOS-G APPROVED BOSTROM SOLAR PROTON MONITOR ITOS-G -01 254 NESS STAFF SCANNING RADICMETER (SR) ITOS-G -02 255 NESS STAFF VERY HIGH RESCLUTION RADIOMETER (VHRR) ITOS-G -03 256 NESS STAFF VERTICAL TEMPEPATURE PROFILE RACIOMETER ITOS-G -04 256 (VTPR)

APPROVED 257 ITOS-H UNITED STATES NOAA-NESS 4 OTR 76 GEOCENTRIC ITOS-H UNITED STATES NASA-OSS NESS STAFF ADVANCEC VERY HIGH RESOLUTION ITOS-H -01 258 RADIOMETER (AVHRR) NESS STAFF TIRCS OPERATIONAL VERTICAL SOUNDER ITOS-H -02 258 (TOVS) SHENK SPACE ENVIRONMENTAL MONITCR (SEM) ITOS-P -04 259 UNKNOWN DATA COLLECTION AND PLATFORM LOCATION ITOS-H -03 259 SYSTEM (UCS)

APPROVED 260 ITOS-I UNITEC STATES NOAA-hESS 2 OTR 78 GEOCENTRIC ITOS-I UNITED STATES NASA-OSS NESS STAFF ADVANCED VERY HIGH RESOLUTICN ITOS-I -01 260 RACIUMETER (AVHRR) NESS STAFF TIRCS OPERATIONAL VERTICAL SOUNDER ITOS-I -02 261 (TOVS) 261 UNKNOWN DATA COLLECTICON AND PLATFORM LCCATION ITOS-1 -03 SYSTEM (UCS)

APPROVED 262 ITOS-J UNITED STATES NASA-OSS 12/01/79 GEOCENTRIC ITOS-J UNITED STATES NOAA-NESS NESS STAFF ADVANCED VERY HIGH RESOLUTION ITOS-J -01 263 RADIOMETER (AVHRR) NESS STAFF TIRCS OPERATICNAL VERTICAL SCONDER ITOS-J -02 263 (TCVS) 264 UNKNOWN DATA COLLECTION AND PLATFCRM LCCATICN ITOS-J -03 SYSTEM (OCS)

APPROVED 1024 IUE UNITED STATES NASA-CSS 2HALF 76 GEOCENTRIC SAS-D

1101 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * 448et************+***t###***************5**t##**************e *#s** **** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

INTERNATIONAL ESRO UNITED KINGDOM SRC NONE ASSIGNED IUE LOW/HIGH RESOLUTION, ULTRAVIOLET SAS-D -01 1025 SPECTROGRAPH PACKAGE

LAGEOS UNITED STATES NASA-CA 1 QTR 76 GEOCENTRIC LAGEOS APPROVED 1026

LARGE SPACE TELESCOPE SEE LST

LASER GEODYNAMIC SAT. SEE LAGEOS

LEM 12 SEE APOLLOC 12 LM/ALSEP

LEM 14 SEE APOLLC 14 LM/ALSEP

LEM 15 SEE APOLLC 15 LM/ALSEP

LEM 16 SEE APOLLC 16 LM/ALSEP

LEM 17 SEE APOLLO 17 LM/ALSEF

LST UNITED STATES NASA-OSS 00/CO/80 GEOCENTRIC LST PROPOSED 1027

LUNAR POLAR ORB-DAUGHTER UNITED STATES NASA-OSS PROPSD79 SELENOCENTRIC LPO-D PROPOSED 1028

LUNAR POLAR ORB-MCTHER UNITED STATES NASA-OSS PROPS079 SELENOCENTRIC LPO-M PROPOSED 1028

MARINER 10 UNITED STATES NASA-OSS 11/03/73 VENUS FLYBY 73-085A 11/03/73 NORMAL STD 1029 BRIDGE MEASUREMENT OF PLASMA ENVIRONMENT 73-085A-03 11/03/73 NORMAL STD 1030 BROADFOOT EUV SPECTROSCOPY 73-085A-05 11/03/73 NORMAL STD 1030 CHASE. JR. TWO-CHANNEL IR RADIOMETER 73-085A-06 11/03/73 NORMAL STD 1031 HOWARD S- AND X-BAND RADIO PROPAGATION 73-085A-02 11/03/73 NORMAL STD 1031 MURRAY TELEVISION PHOTOGRAPHY 73-085A-01 04/03/74 INOPERABLE ZERO 1032 NESS FLUXGATE MAGNETCOMETER 73-085A-04 11/03/73 NORMAL STD 1032 SIMPSON ENERGETIC PARTICLES 73-085A-07 11/03/73 NORMAL STD 1032

MARINER 73 SEE MARINER 10

MARINER 77A UNITED STATES NASA-OSS 2HALF 77 JUPITER FLYBY MARN77A APPROVED 1033 BLAMONT LYMAN ALPHA SPECTROPHOTOMETER MARN77A-12 1033 BRIDGE PLASMA MARN77A-06 273 BROADFOOT ULTRAVIOLET SPECTROSCOPY MARN77A-04 272 ESHLEMAN COHERENT S- AND X-BAND TRANSMITTER AND MARN77A-02 271 S-BAND RECEIVER HANEL INFRARED SPECTROSCOPY AND RACIOMETRY MARN77A-03 271 KRIMIGIS LOW-ENERGY CHARGED PARTICLE ANALYZER AND MARN77A-07 273 TELESCOPE LILLIE MULTIFILTER PHOTOPOLARIMETER. MARN77A-11 275 2201-7300 A

1102 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRENT STATE------COUNTRY AND AGENCY DATE ORBIT TYPE * * SPACECRAFT NAME DATA PAGE *********************************************4*************** ********** NSSOC ID EPOCH STATUS RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME MMDDYY

272 NESS TRIAXIAL FLUXGATE MAGNETOMETERS MARN77A-05 27) SMITH TV PHOTOGRAPHY MARN77A-01 274 SOUERMAN INTERPLANETARY CUST PARTICLE MEASUREMENT MARN77A-09 274 VOGT HIGH- AND MODERATELY LOW--ENERGY MARN77A-08 COSMIC-RAY TELESCOPE 275 WARWICK SWEEP FREQUENCY (0.02 TO 40 MHZ) RADIC MARN77A-10 RECEIVER

FLYBY MARN778 APPROVED 1034 MARINER 778 UNITED STATES NASA-OSS 2HALF 77 JUPITER 1034 6LAMONT LYMAN ALPHA SPECTROPHOTCMETER MARN770-12 MARN77U-06 279 BRIDGE PLASMA 278 BROADFOOT ULTRAVIOLET SPECTROSCOPY MARN77E-04 277 ESHLEMAN COHERENT S- AND X-BAND TRANSMITTER AND MARN778-02 S-BAND RECEIVER 277 HANEL INFRARED SPECTRCSCOPY AND RADICMETRY MARN778-03 279 KRIMIGIS LO*-ENERGY CHARGED PARTICLE ANALYZER AND MARN770-07 TELESCOPE 281 LILLIE MULTIFILTER PICTOPOLAR[1ETER. MARN77E-11 22C0-7300 A 278 NESS TRIAXIAL FLUXGATE MAGNETCOMETERS MARN77e-05 276 SMITH TV PHOTOGRAPHY MARN778-01 283 SOBERMAN INTERPLANETARY CUST PARTICLE MEASUREMENT MARN77E-09 280 VOGT HIGH- AND MODERATELY LCOW-ENERGY MARN778-08 COSMIC-RAY TELESCOPE 281 WARWICK SWEEP FREQUENCY (0.02 TC 40 MHZ) RADIO MARN77B-10 RECEIVER

MARINER JUPITER/SATURN A SEF MARINER 77A

MARINER JUPITER/SATURN E SEE MARINER 778

MARINER VENUS/MERCURY SEE MARINER 10

MARINER-J VENUS/MERCURY SEE MARINER 10

METEC SEE METEOROID TECHNOLCGY SAT

GEOCENTRIC 72-061A 08/27/72 PARTIAL SUBS 106 METEUROID TECHNOLCGY SAT UNITED STATES NASA-CAST 08/13/72 72-061A-01 03/11/74 NORMAL SUBS 106 KINARD METEOROID PENETRATION

METEOROLOGICAL SATELLITE SEE METECOAT

METOSAT APPROVED 1035 METEOSAT INTERNATIONAL ESRC 4 QTR 76 GEOCENTRIC

MOTHER SEE ISEE-A

MTS SEE METECROID TECHNOLCOGY SAT

1103 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH * CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE C ~~****~~***#s4s t*4 ate a********************** **** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

NEUTRAL POINT EXPLCRER SEE HAWKEYE

NIMBUS 4 UNITED STATES NASA-GA 04/08/70 GEOCENTRIC 70-025A 04/08/71 PARTIAL SUBS 42 COTE INTERROGATION. RECORDING. AND LOCATION 70-025A-07 04/08/71 PARTIAL SUBS 45 SYSTEM (IRLS) HEATH SCLAR UV MONITOR 70-025A-01 03/11/74 NORMAL SUBS 44 HEATH BACKSCATTER ULTRAVIOLET (BUV) 70-025A-05 04/08/71 PARTIAL SUBS 44 SPECTROMETER

NIMDUS 5 UNITED STATES NASA-OA 12/11/72 GEOCENTRIC 72-097A 01/04/73 PARTIAL STD 127 HOUGHTON SELECTIVE CHOPPER RADIOMETER (SCR) 72-097A-02 12/11/72 NORMAL STD 128 MNCCULLOCH TEMPERATURE/HUMIDITY INFRARED RADIOMETER 72-097A-08 12/11/72 NORMAL STD 130 (THIR) SMITH INFRARED TEMPERATURE PROFILE RACICMETER 72-097A-01 01/00/73 PARTIAL STD 128 (ITPR) STAELIN NIMEUS-E MICRChAVE SPECIRCMETER (NEMS) 72-097A-03 12/11/72 NORMAL STD 129 WILHEIT, JR. ELECTRICALLY SCANNING MICROWAVE 72-097A-04 12/11/72 NORMAL STD 129 RADICMETER (ESMR)

NIMBUS-D SEE NIMBE 4

NIMBUS-E SEE NIMBUS 5

NIMBUS-F UNITED STATES NASA-OA 10/00/74 GEOCENTRIC NIMBS-F APPROVED 289 BANDEEN TEMPERATURE/HUMIDITY INFRARED RADIOMETER NIMBS-F-12 294 (THIR) GILLE LIMB RADIANCE INVERSION RADIOMETER NIMBS-F-04 292 (LRIR) HOUGHTON PRESSURE-MODULATED RADICMETER (PMR) NIMBS-F-09 293 KELLOGG TROPICAL WIND ENERGY CONVERSION AND NIMBS-F-01 290 REFERENCE LEVEL EXPERIMENT (TWERLE) MCCULLOCH HIGH RESOLUTICN INFRARED RADIATION NIMBS-F-02 291 SOUNDER (HIRS) SMITH EARTH RADIATICO BUDGET (ERB) NIMBS-F-05 292 STAELIN SCANNING MICRCAVE SPECTROMETER (SCAMS) NIMBS-F-10 294 VONBUN TRACKING AND CATA RELAY NIMBS-F-13 295 WILHEIT. JR. ELECTRICALLY SCANNING MICFOWAVE NIMBS-F-03 291 RADIOMETER (ESMR)

NIMBUS-G UNITED STATES NASA-CA 1 OTR 77 GEOCENTRIC NIMBS-G APPROVED 1035

NOAA 2 UNITED STATES NOAA-NESS 10/15/72 GEOCENTRIC 72-082A 10/15/72 NORMAL STD 116 UNITED STATES NASA-CA BOSTROM SOLAR PROTON MCNITOR 72-082A-01 10/15/72 NORMAL STD 117 NESS STAFF SCANNING RADICMETER (SR) 72-082A-02 10/15/72 NORMAL STO tIT NESS STAFF VERY HIGH RESCLUTION RACICMETER (VHRR) 72-082A-03 10/15/72 NORMAL STD i18

1104 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENT BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

*LAUNCH ------CURRENT STATE------NAME COUNTRY AND AGENCY DATE ORBIT TYPE * 4 SPACECRAFT DATA PAGE ###+ *****t~tt**** t*f*********** *ssttttt NSSDC ID EPOCH STATUS * MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME

GEOCENTRIC 73-086A 11/29/73 NORMAL STD 250 NOAA 3 UNITED STATES NOAA-NESS 11/06/73 UNITED STATES NASA-OA 25i BOSTROM SOLAR PROTON MCrITOR 73-086A-01 11/06/73 NORMAL STD 73-086A-02 03/15/74 PARTIAL UNKN 252 NESS STAFF SCANNING RADIOMETER (SR) 73-086A-03 03/15/74 NORMAL STD 252 NESS STAFF VERY HIGH RESCLLTION RADIOMETER (VHRR) 73-086A-04 03/15/74 PARTIAL UNKN 253 NESS STAFF VERTICAL TEMPERATURE PROFILE RACIOMETER (VTPR)

NRL-111 SEE SOLRAC 11A

NRL-1I1 SEE SOLRAD 118

72-065A 08/21/72 NORMAL STD 107 OAD 3 UNITED STATES NASA-OSS 08/21/72 GEOCENTRIC 72-065A-02 06/00/73 PARTIAL STD 108 BOYD STELLAR PHOTOMETRY 72-065A-01 08/21/72 NORMAL STD 108 SPITZER HIGH RESOLUTION TELESCOPES

OAO-C SEE OACO

GEOCENTRIC 71-083A 05/18/73 NORMAL SUBS 80 OSO 7 UNITED STATES NASA-OSS 09/29/71 71-083A-04 05/18/73 NORMAL SUBS 82 CLARK COSMIC X-RAY SOURCES IN THE RANGE i.5 TO 9 A 71-083A-01 05/18/73 PARTIAL SUBS 80 NEUPERT X-RAY AND EUV SFECTROhELICGRAPH (2 TO 400 A) 71-083A-03 05/18/73 NORMAL SUBS 82 PETERSON COSMIC X-RAY EXPERIMENT 71-083A-05 09/29/73 NORMAL STD 83 PETERSON HARD SOLAR X-RAY MONITORING 71-083A-02 09/00/73 PARTIAL SUBS 81 TUUSEY WHITE-LIGHT CCRCNCGRAPH AND EXTREME ULTRAVIOLET CORONOGRAPH

OSO-EYE SEE OSC-I

OSO-H SEE 050 7

GEOCENTRIC OSO-I APPROVED 295 OSO-I UNITED STATES NASA-OSS 03/00/75 OSO-I -06 298 BOLOT COSMIC X-RAY SPECTROSCOPY -01 296 bRUNER, JR. HIGH RESOLUTICON ULTRAVIOLET SFECTROETEP OSO-I MEASUREMENTS -04 297 CULHANE MAPPING X-RAY HELICMETEP OSO-1 -07 298 FROST HIGH-ENERGY CELESTIAL X RAYS OSO-I 297 KRAUSHAAP SOFT X-RAY BACKGRCUND RADIATICN OSO-I -05 INVESTIGATION OSO-1 -02 296 LEMAIRE CFRCMOSPHERE FINE STRUCTURE STUDY OSO-I -03 296 NOVICK HIGH-SENSITIVITY GRAPHITE CRYSTAL SPECTROSCOPY OF STELLAR AND SOLAR X RAYS -08 298 WELLER, JR. EUV FROM EARTH AND SPACE OSO-I

OUTER PLANETS A SEE MARINER 77A

OUTER PLANETS B SEE MARINER 778

1105 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * ************************************** **NSSCC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

OV5-6 UNITED STATES DOD-USAF 05/23/69 GEOCENTRIC 69-0468 05/23/69 NORMAL STD 30 YATES GEIGER-MUELLER TUBE. SOLAR X-RAY 69-0468-01 05/23/69 NORMAL STD 30 OETECTOR, 2 TC 12 A YATES SCDIUM IODIDE SCINTILLATCF, GAMMA-RAY 69-0468-02 05/23/69 NORMAL STD 30 DETECTOR. I1 TO 1175 KEV YATES PROTON ALPHA PARTICLE TELESCOPE 69-046B-03 08/12/72 NCRMAL SUBS 31 YATES LOW-ENERGY ELECTRON DETECTOR 69-046B-05 05/23/69 NORMAL STO 31

P 73-4 SEE ELMS I

P 74-3 SEE ELMS 2

PIONEER 6 UNITED STATES NASA-OSS 12/16/65 HELIOCENTRIC 65-105A 02/07/71 NORMAL SUBS 3 BRIDGE SOLAR WIND PLASMA FARADAY CUP 65-105A-02 02/07/71 NORMAL SUBS 4 ESHLEMAN TWO-FREQUENCY RADIO RECEIVER 65-105A-C4 02/07/71 NORMAL SUBS 5 FAN COSMIC-RAY TELESCOPE 65-105A-03 10/22/67 PARTIAL SUBS 5 MCCRACKEN COSMIC-RAY ANISOTROPY DETECTION 65-105A-05 05/21/66 NORMAL SUBS 6

PIONEER 7 UNITED STATES NASA-CSS 08/17/66 HELIOCENTRIC 66-075A 08/17/66 NORMAL STD 6 MCCRACKEN COSMIC-RAY ANISOTROPY 66-075A-05 02/09/69 PARTIAL SUBS 9 SIMPSON COSMIC-RAY TELESCOPE 66-075A-06 05/26/69 PARTIAL SUBS 9 WOLFE ELECTROSTATIC ANALYZER 66-075A-03 02/16/69 PARTIAL SUBS B

PIONEER 8 UNITED STATES NASA-OSS 12/13/67 HELIOCENTRIC 67-123A 01/25/71 NORMAL SUBS 10 BERG COSMIC DUST DETECTOR 67-123A-04 01/25/71 NORMAL SUBS 13 ESHLEMAN TWO-FREQUENCY BEACON RECEIVER 67-123A-03 01/25/71 NORMAL SUBS 13 MCCRACKEN COSMIC-RAY ANISCTROPY 67-123A-05 01/25/71 NORMAL SUBS 14 NESS SINGLE-AXIS MAGNETCMETER 67-123A-01 01/25/71 NORMAL SUBS 11 WEBBER COSMIC-RAY GRADIENT DETECTOR 67-123A-06 01/25/71 NORMAL SUBS 15 WOLFE ELECTROSTATIC ANALYZER 67-123A-02 31/25/71 PARTIAL SUBS 12

PIONEER 9 . UNITEC STATES NASA-CSS 11/08/68 HELIOCENTRIC 68-100A 05/19/69 NORMAL SUBS 17 BERG COSMIC DUST DETECTOR 68-100A-G04 5/19/69 NORMAL SUBS 20 ESHLEMAN TWO-FREQUENCY BEACON RECEIVER 68-100A-03 05/19/69 PARTIAL STD 19 MCCRACKEN COSMIC-RAY ANISOTROPY 68-100A-05 05/19/69 NORMAL SUBS 20 SCARF PLASMA WAVE DETECTCR 68-100A--07 05/19/69 NORMAL SUDS 22 SONETT THREE-AXIS MAGNETOMETER 68-I00A-01 05/19/69 NORMAL SUBS 18 WEBBER COSMIC-RAY TELESCCPE 68-1COA-06 05/19/69 NORMAL SUDS 21 WOLFE ELECTROSTATIC ANALYZER 68-100A-02 05/19/69 PARTIAL SUBS 18

PIONEER 10 UNITED STATES NASA-CSS 03/02/72 JUPITER FLYBY 72-012A 03/03/72 NORMAL STD 1036 ANDERSON CELESTIAL MECHANICS 72-012A-09 03/03/72 NORMAL STD 94 FILLIUS JOVIAN TRAPPEC RADIATION 72-012A-05 03/03/72 NORMAL STD 92 GEHRELS IMAGING PHOTOPOLARIMETER (IPP) 72-012A-07 03/03/72 NORMAL STD 1037 JUDGE ULTRAVIOLET PHOTCMETRY 72-012A-06 03/03/72 NORMAL STD 93 KINARD METEOROID DETECTORS 72-012A-04 03/03/72 NORMAL STD 92 KLIORE S-BAND OCCULTATION 72-012A-10 03/03/72 NORMAL STD 95

1106 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

SLAUNCH * ------CURRENT STATE ------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * PAGE sestat#** +#***+*************** NSSDC ID EPOCH STATUS DATA * MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME

72-012A-12 03/02/72 NORMAL STD 96 MCDONALD COSMIC-RAY SPECTRA 72-012A-02 03/03/72 NORMAL STD 91 SIMPSON CHARGED PARTICLE COMPOSITION 03/03/72 NORMAL STD 90 SMITH MAGNETIC FIELDS 72-012A-01 03/03/72 NORMAL STD 91 SOBERMAN ASTEROID/METECROID ASTRCNCMY 72-012A-03 03/03/72 NORMAL STD 95 VAN ALLEN JOVIAN CHARGED PARTICLES EXPERIMENT 72-012A-11 02/27/74 NORMAL UNKN 1038 WEINBERG ZCODIACAL-LIGHT TWO-COLOR 72-012A-14 PHTOPCLARIMETRY WOLFE PLASMA EXPERIMENT 72-012A-13 03/03/72 NORMAL STD 96

FLYBY 73-019A 04/06/73 NORMAL STD 1038 PIONEER 11 UNITED STATES NASA-CSS 04/06/73 JUPITER 73-019A-09 04/06/73 NORMAL STO 135 ANDERSON CELESTIAL MECHANICS 73-01A-05 04/06/73 NORMAL STD 133 FILLIUS JOVIAN TRAPPEC RADIATION 04/06/73 NORMAL STD 1039 GEHRELS IMAGING PHOTOFOLARIMETE9 73-019A-07 04/06/73 NORMAL STD 134 JUDGE ULTRAVIOLET PfOTCMETRY 73-019A-06 04/06/73 NORMAL STD 133 KINARD METEOROID DETECTOR 73-019A-04 73-019A-10 04/06/73 NORMAL STD 135 KLIORE S-BAND OCCULTATION 04/06/73 NORMAL STD 136 MCDONALD COSMIC-RAY SPECTRA 73-019A-12 04/06/73 NORMAL ZERO 135 MUNCH INFRARED RACICMETER 73-019A-08 73-019A-14 04/06/73 NORMAL SUBS 137 NESS JOVIAN MAGNETIC FIELD 04/06/73 NORMAL STD 132 SIMPSON CHARGED PARTICLE COMPOSITION 73-019A-02 04/06/73 NORMAL STD 131 SMITH MAGNETIC FIELDS 73-019A-01 04/06/73 NORMAL STD 132 SOBERMAN ASTEROID/METECPCID ASTPCNCMY 73-019A-03 04/06/73 NORMAL STD 136 VAN ALLEN JOVIAN CHARGED PARTICLES EXPERIMENT 73-019A-11 02/27/74 NORMAL UNKN 1040 WEINBERG ZODIACAL-LIGHT TWO-COLOR 73-019A-15 PHOTOPCLARIMETRY STD 137 WOLFE PLASMA EXPERIMENT 73-0194-13 04/06/73 NORMAL

PIGNEER VENUS 1978 SEE PIONEER VENUS PFCEE A

PIONEER VENUS 1978 SEE PIONEER VENUS PFOBE b

PIONEER VENUS 1978 SEE PIONEER VENUS PROBE C

PIONEER VENUS 1978 SEE PIONEER VENLS PFCOE 0

PIONEER VENUS 1978 SEE PIONEER VENUS PCROBE E

PIONEER VENUS 1978 ORBIT SFE PIONEER VENUS CORBITER

PIONEER VENUS LARG POOBE SEE PIONEER VENLS PROBE E

PIO780R PROPOSED 299 PIONEER VENUS ORBITER UNITED STATES NASA-OSS 08/00/78 VENUSCENTRIC

PIO78PA PROPOSED 299 PIONEER VENUS PROBE A UNITED STATES NASA-CSS 05/00/78 VENUS FLYBY 301 KNUDSEN RETARDING POTENTIAL ANALYZER PIO7BPA-C4 300 NAGY LANGMUIR PROEE PIO78PA-01 302 PETTENGILL DIFFERENTIAL VEFY-LONG-EASELINE PIO78PA-06 INTERFEROMETRIC TRACKING

1107 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH ------CURRENT STATE------SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * ************************************ NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

STEWART ULTRAVIOLET SPECTROMETER PIO78PA-05 302 ,TAYLOR. JR. ION MASS SPECTRCMETER PIO78PA-02 301 VON ZAHN NEUTRAL PARTICLE MASS SPECTRCMETER PIO78PA-03 301

PIONEER VENUS PROBE 0 UNITED STATES NASA-CSS 05/00/78 VENUS LANDER PIO78PB PROPOSED 302 dLAMONT CLOUD EXTENT. STRUCTURE, AND PIOTBPB-02 304 DISTRIBUTION KNOLLENBERG CLOUD PARTICLE SIZE SPECTrFOETER PIOT8PB-03 304 DYAMA GAS CHROMATOGRAPH PIO78PB-04 304 PETTENGILL DIFFERENTIAL VERY-LONG-EASELINE PIO78PB-09 306 INTERFEROMETRIC TRACKING SEIFF ATMOSPHERE STRLCTURE PIO78PB-01 303 SPENCER NEUTRAL PARTICLE MASS SPFECTRCMETER PIO78PB-Ob 305 SUUMI INFRARED RADICMETER PI078P8-05 305 TOMASKO SCLAR ENERGY PENETRATION INTO THE PIO78PB-07 305 ATMOSPHERE WEINMAN SPIN-SCAN PHOTOMETER P1078PB-08 306

PIONEER VENUS PROBE EUS SEE PICNEER VENUS PROEE A

PIONEER VENUS PROBE C UNITED STATES NASA-CSS 05/00/78 VENUS LANDER PIO78PC PROPOSED OLAMONT CLOUD EXTENT. STRUCTURE. 307 AND PIO78PC-02 308 DISTRIBUTION PETTENGILL DIFFERENTIAL VEFY-LONG-EASELINE PIO78PC-03 308 INTERFEROMETRIC TRACKING SEIFF ATMOSPHERE STRUCTURE P1O78PC-01 307

PIONEER VENUS PROBE 0 UNITED STATES NASA-CSS 05/00/78 VENUS LANDER PIO78PD PROPOSED BLAMONT CLOUD EXTENT. STRUCTURE. 308 AND PIO78PO-02 310 DISTRIBUTION PETTENGILL DIFFERENTIAL VERY-LONG-BASELINE PIO78PD-03 310 INTERFEROMETRIC TRACKING SEIFF ATMOSPHiERE STRUCTURE PIOTB78PD-01 309

PIONEER VENUS PROBE E UNITED STATES NASA-CSS 05/00/78 VENUS LANDER PIO78PE PROPOSED 310 BLAMONT CLOUD EXTENT. STRUCTUREAND DISTRIBUTION PIO78PE-02 311 PETTENGILL DIFFERENTIAL VERY-LONG-EASELINE PIO78PE-03 312 INTERFEROMETRIC TRACKING SEIFF ATMOSPHERE STRUCTURE PIO78PE-01 311

PIONEER VENUS SMAL PROBE SEE PIONEER VENUS PROBE C

PIONEER VENUS SMAL PROBE SEE PIONEER VENUS PROBE 0

PIONEER VENUS SMAL PROBE SEE PIONEER VENUS PROBE E

PIONEER-A SEE PIONEER 6

1108 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS EY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

*LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * NSSDC ID EPOCH STATUS DATA PAGE ******************** ****'****,***t* * MMDDYY RATE NO. *PRINC.INVEST.NAME EXPERIMENT NAME *

PIONEER-B SEE PICNEER 7

PIONEER-C SEE PICNEER 8

PIONEER-D SEE PIOCNEER 9

PIONEER-F SEE PIONEER 10

PIONEER-G SEE PIONEER 11

RADIO ASTRONOMY EXPLORER SEE RAE-E

NORMAL STO 140 RAE- UNITEC STATES NASA-CSS 06/10C/73 GEOCENTRIC 73-039A 06/10/73 NORMAL STD 140 STONE STEP FREQUENCY RADIOMETERS 73-039A-01 06/10/73 NORMAL STD 141 STONE RAPID-BURST RECEIVERS 73-039A-02 06/10/73 06/10/73 NORMAL STD 141 STONE CAPACITANCE PROEE 73-039A-03

RELATIVITY SEE GP-A

APPROVED 1041 RM 20 UNITED STATES DOD-USAF 11/01/74 GEOCENTRIC RM20

ROVER 15 SEE APOLLC 15 LM/ALSEF

ROVER 16 SEE APOLLC 16 LM/ALSEF

ROVER 17 SEE APOLLC 17 LM/ALSEF

S 6C SEE AE-C

S 60 SEE AE-D

S 6E SEE AE-E

71-096A 11/15/71 NORMAL STD 83 S-CUBED A UNITED STATES NASA-OSS 11/15/71 GEOCENTRIC PARTIAL SUBS 85 CAHILL. JR. SEARC- COIL MAGNETOMETEW 71-096A-05 04/01/73 NORMAL STD 85 FRITZ SCLIO-STATE PRUTON-ALPHA PARTICLE 71-096A-02 11/15/71 TELESCOPE PARTIAL SUBS 86 GURNETT AC ELECTRIC FIELD MEASUREMENT 71-096A-07 05/01/73 NORMAL STD 84 HOFFMAN CHANNEL ELECTRUO MULTIPLIERS WITH 71-096A-01 11/15/71 ELECTROSTATIC ANALYZERS NORMAL STD 85 WILLIAMS SCLID-STATE DETECTORS 71-096A-03 11/15/71

S3-1 SEE SECSP F72-5

S3-3 SEE SESP 74-2

74-0CA 02/18/74 NORMAL STD 319 SAN MARCO 4 UNITED STATES NASA-GSS 02/18/74 GEOCENTRIC ITALY CRA

1109 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH ------CURRENT STATE------* SPACECRAFT NAME CCUNTRY AND AGENCY DATE ORBIT TYPE *********************************************************************************** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

BROGLIO ATMOSPHERIC CRAG DENSITY ACCELERCMETER 74-009A-01 03/12/74 PARTIAL UNKN 319 NEWTON NEUTRAL ATMOSPHERE COMPOSITION 74-OC9A-02 03/12/74 NORMAL STD 320 SPENCER NEUTRAL ATMOSFhERE TEMPERATLRE 74-009A-03 03/12/74 NORMAL STD 320

SAN MARCO C-2 SEE SAN MARCC 4

SARI FRANCE 00/00/76 GECCENTRIC SARI PROPOSED 312

SAS I SEE SAS-A

SAS-A UNITEC STATES NASA-OSS 12/12/70 GECCENTRIC 70-107A 01/23/71 PARTIAL SUBS 54 GIACCONI ALL-SKY X-RAY SURVEY 70-107A-01 04/00/73 PARTIAL SUBS 55

SAS-C UNITED STATES NASA-GSS 2 GTR 75 GEOCENTRIC SAS-C APPROVED 313 CLARK ANALYSIS OF EXTRAGALACTIC X-RAY SOURCES SAS-C -01 313 CLARK ANALYSIS OF GALACTIC X-RAY SOURCES SAS-C -02 314 CLARK CONTINUOUS X-RAY FLUCTUATION MONITOR CF SAS-C -03 314 SCO X-1 CLARK X-RAY AESORPTION CONTOURS OF THE GALAXY SAS-C -04 315

SAS-D SEE IUE

SATS SEE HCMM

SE-C SEE SOLRAD 10

SESP 74-2 UNITFD STATES DOD-USAF 08/00/75 GEOCENTRIC ST74-2A APPROVED 1041

SESP NO.NRL-111-0264 SEE SOLRAC 11A

SESP NO.NRL-111-0264 SEE SOLRAD 118

SESP P72-2A SEE RM 2C

SESP P73-4 SEE ELMS 1

SESP P73-5 UNITED STATES DOD-USAF 08/00/74 GEOCENTRIC ST73-5A APPROVED 1042

SESP P74-3- SEE ELMS 2

SIRIO-A ITALY 2 QTR 75 GEOCENTRIC SIRIO-A APPROVED 317

SMALL APPLICATIONS TECH SEE HCMM

SMM SEE SOLAR MAXIMUM MISSION

SMS-A UNITED STATES NOAA-NESS 05/30/74 GEOCENTRIC SMS-A APPROVED 320 UNITEC STATES NASA-OA

1110 CUNULATIVE INDEX OF ACTIVE AND PLANNED SPACECFAFT AND EXPERIMENTS EY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME CCUNTRY AND AGENCY DATE ORBIT TYPE * #** ******************************S***** NSSDC 10 EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMODYY RATE NO.

NESS STAFF VISIHLE-INFRARED SPIN-SCAN RACICMETER SMS-A -01 321 (VISSR) UNKNOWN METEDROLOGICAL CATA COLLECTION AND SMS-A -05 323 TRANSMISSION SYSTEM WILLIAMS ENERGETIC PARTICLE MONITOR SMS-A -02 322 WILLIAMS SOLAR X-RAY MONITOR SMS-A -03 322 WILLIAMS MAGNETIC FIELD MCNITCR SMS-A -04 323

SMS-B UNITEC STATES NOAA-NESS 07/00/74 GEOCENTRIC SMS-B APPROVED 323 UNITED STATES NASA-CA NESS STAFF VISIBLE-INFRAREC SPIN-SCAN RACICMETER SMS-8 -04 325 (VISSR) UNKNCWN METECFOLOGICAL CATA CCLLECTICN ANC SMS-B -05 326 TRANSMISSION SYSTEM WILLIAMS ENERGETIC PARTICLE MCNITOR SMS-e -01 324 WILLIAMS SOLAR X-RAY MCNITOR SMS-8 -02 325 WILLIAMS MAGNETIC FIELC MOCNTOR SMS-B -03 325

SMS-C UNITEC STATES NOAA-NESS AUG. 74 GEOCENTRIC SMS-C APPROVED 327 UNITEC STATES NASA-CA NESS STAFF VISIBLE-INFRAREC SPIN-SCAN RADICMETER SMS-C -01 327 (VISSR) WILLIAMS ENERGETIC PARTICLE MONITOR SMS-C -02 328 WILLIAMS SOLAR X-RAY MONITOR SMS-C -03 328 WILLIAMS MAGNETIC FIELD CONITOR SMS-C -04 329

SOLAR EXPLORER-C SEE SOLRAC IC

SOLAR MAXIMUM MISSION UNITED STATES NASA-OSS MID 1978 GEOCENTRIC SMM PROPOSED 1042

SOLRAD 9 UNITED STATES NASA-CSS 03/05/68 GECCENTRIC 68-017A 02/25/74 PARTIAL SUBS 16 UNITEC STATES DOD-NAVY KREPLIN SOLAR RADIATICN DETECTORS 68-017A-01 02/25/74 PARTIAL SUBS 15

SOLRAD 10 UNITED STATES NASA-CSS 07/08/71 GEOCENTRIC 71-O58A 07/00/73 NORMAL SUBS 74 UNITED STATES DOD-NAVY KREPLIN SOLAR RADIATICN DETECTORS 71-058A-01 12/11/73 NORMAL SUBS 75 KREPLIN ALL-SKY X-RAY SURVEY 71-058A-C2 07/00/73 NORMAL SUBS 76

SOLRAD 11A UNITEC STATES DOD-hAVY 03/CO/75 GECCENTRIC SRD-11A APPROVED 1043 BLAKE SOLAR PROTONS SRD-IIA-14 2043 BLAKE OMNIDIRECTIONAL PROTONS SRO-11A-17 1044 BLAKE ANTISOLAR PRCTONS SRU-11A-23 1044 -HYkAM STELLAR/AURORAL X RAYS SRO-IIA-16 1045 O0SCHEK THOMSON X-RAY POLARIMETER SRD-11A-10 1045 FELDMAN 1175- TO 1800-A SCLAR UV SPECTRCMETER SRD-11A-09 1046 FRITZ 15- TO 150-KEV SOLAR X-RAY MONITOR SRD-11A-01 1046 FRITL X-PAY RACKCRCLNC SRD-11A-24 1046

1111 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS RY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * *r*9tC* **t*t*e ***444*t4*4**4*t4 *s***4* **** ************ *4 *4*4* NSSOC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAM7 EXPERIMENT NAME * MMDDYY RATE NO.

KELLEY PROTON-ALPHA TELESCOPE SRD-IIA-20 1047 KELLEY LOa-ENERGY PRCTCN SPECTROMETER SRD-11IA-21 1047 KREPLIN 1- TO 8-A SOLAR X-MAY MONITOR SRD-I11A-04 1047 KREPLIN 8- TO 16-A SCLAR X-RAY MONITCR SRD-11A-05 1048 KREPLIN 44- TO 60-A SCLAR X-RAY MCNITCR SRD-IIA-06 1048 KREPLIN 172- TO 1050-A SOLAR EUV MONITOR SRD-IIA-07 1049 KkEPLIN IC8C- TO 1350-A SOLAR UV MCNITOR SRD-11A-08 1049 KREPLIN 0.5- TO 3-A SOLAR X-RAY MCNITCR SRD-IIA-12 1049 KREPLIN 1- TO 20-A SCLAR X-RAY MONITOR SRD-IIA-13 1050 MEEKINS CCNTINULM (8.8 A) AND MAGNESILM LINE SRD-11A-03 1050 (9.17 A AND 8.42 A) MCNITOR MEEKINS BREGG X-RAY PCLAPIMETER SRD-IIA-11 1051 SMATHERS X-RAY MONITOR (0O1-1Ie A. 0.5-3 A. SRD-11A-02 1051 1-4 A) VAMPOLA SCLAR FLARE ELECTRONS SRD-11A-22 1051 WELLFR. JR. GEOCORONAL-EXTRATERRESTRIAL EUV - SRD-IIA-18 1052 CETECTOR 1 WELLER, JR. GEtCURONAL-EXTRATERRESTRIAL EUV - SRD-11A-19 1052 DETECTOR 2

SOLRAD 11 UNITED STATES DOD-NAVY 03/00/75 GEOCENTRIC SRD-116 APPROVED 1052 BLAKE SOLAR PROTONS 5RD-118-14 1053 BLAKE OMNICIRECTIONAL PROTONS SRO-118-17 1054 DLAKE ANTISOLAR PROTCNS SRD-118-23 1054 8YRAM STELLAR/AURORAL X-RAYS SRD-116-e1 1054 DOSCHEK THUMSON X-RAY PCLARIMETER SRO-118-10 1055 FELOMAN 1175- TO 1800-A SOLAR UV SPECTRCMETER SRD-118-09 1055 FRITZ 15- TC 15r-KEV SCLAR X-RAY MONITOR SRD-118-01 1056 FRITZ X-RAY BACKGRCLNC SRD-118-24 1056 KELLEY PRUTON-ALPHA TELESCOPE SRD-118-20 1057 KLLEY LOW-ENERGY PRCTEN SPECTROMETER SRD-118-21 1057 KREPLIN I- TO 8-A SOLAR X-RAY MOCNITCR SHO-112-04 1057 KREPLIN H- TC 16-A SOLAR X-RAY MONITOR SRD-118-05 1058 KRCPLIN 44- TO O0-A SOLAR X-RAY MONITOR SRD-118-06 1058 KREPLIN 176- TO 1050-A SOLAR EUV MONITOR SRD-118-07 1058 KRCPLIN lCdC- TO 1350-A SOLAR UV MCONITGR SRD-118-08 1059 KREPLIN 0.5- TO 3- A SOLAR X-RAY MONITOR SRD-118-12 1059 KREPLIN 1- TO 20-A SOLAR X-RAY MONITOR SRD-1I-13 1060 MEEKINS CONTINUUM (8.8 A) AND MAGNESIUM LINE SRO-118-03 1060 (9.17 A PND 8.42 A) MONITOR MEEKINS 6RAGG X-RAY PCLARIMETER SRD-118-11 1060 SMATHER X-PAY MONITOR (0.1-1.6 A. C.5-3 A, SRO-118-02 1061 1-4 A) VAMPOLA SCLAR FLARE ELECTRONS SRO-118-22 1061 WELLER. JR. GEOCRONAL-EXTRATERRESTRIAL EUV - SRD-118-18 1062 CETECTOR I WELLER. JR. GEUCURONAL-EXTRATERRESTRIAL ELV - SRD-11E-19 1062 tDTECTOR 2

1112 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS EY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE CRBIT TYPE * *****s****s*******tt***************#********** ***************************** ********** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMODYY RATE NO.

SOLRAD HI SEE SOLRAD 118

SOLRAD HI-TRIP SEE SOLRAC 11A

SOLRAD HI-TRIP SEE SOLRAC 116

SOLRAD-C SFE SCLRA 10

SPACE SHUTTLE UNITEC STATES NASA-GMSF 12/00/78 GEOCENTRIC SHUTTLE APPROVED 316

SPACELAB INTERNATICNAL ESRO 00/00/79 GEOCENTRIC SPACLAB APPROVED 1062

SRATS JAPAN TOKYO U 1975 GEOCENTRIC SRATS APPROVED 330 FUGONO ICNIC CCMPOSITICON SRATS -07 332 HIRAC ELECTRON TEMPERATURE SRATS -05 331 MATSUOKA SCLAR X-RAY MCNITOR SRATS -01 333 MIYAZAKI PLASMA DIAGNOSIS SRATS -06 331 OHYA ELECTRON DENSITY MEASUREMENT SRATS -04 331 OSHIO HYDROGEN LYMAN-ALPHA SRATS -02 330 TOHMATSU GEOCGRUNAL UV GLOW AND EARTH UV ALBEDC SRATS -03 331 TOHMATSU EARTH ULTRAVICLET ALBEDC SRATS -08 332

SRD-I1A SEE SULRAD IIA

SSS-A SEE S-CUBED A

ST 72-2A SEE RM 20

ST 73-4A SEE ELMS I

ST 74-3A SEE ELMS 2

STP PROBE SEE ISEE-C

SYNC MET. SAT. A SEE SMS-A

SYNC MET. SAT. i SEE SMS-E

SYNCH MTEOHOLOGCL SAT. A SEE SMS-A

SYNCH MTEOROLOGCL StT. E SEE SMS-0

TO I SEE TD IA

TD IA INTERNATICNAL ESRO 03/12/72 GEOCENTRIC 72-014A 02/14/73 NORMAL SUBS 1063 DE JAGEP SOLAR X-RAY MONITOR 72-014A-06 02/14/73 NORMAL SUBS 100 LABEYRIF SPECTROMFTRY CF PRIMARY CHARGED 72-014A-03 02/1%/73 NORMAL SUBS 99 PAPTICLFT

1113 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

* LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE * ***********S****** *******e******** *****************s e*********** **** NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMOOYY RATE NO.

LABEYRIE SPECTROMETRY CF EXTRATERRESTRIAL X RAYS 72-014A-04 07/02/73 NORMAL SU3S 99 LABEYRIE GAMMA-RAY MEASUREMENT 72-014A-07 02/14/73 NORMAL SUBS 10O MONFILS STELLAR UV RACIATION EXPERIMENT 72-014A-01 02/14/73 NORMAL SUBS 1064 OCCHIALINI SOLAR GAMMA RAYS IN THE SC- TO 500-MEV 72-014A-05 02/14/73 NORMAL SUBS 99 ENERGY RANGE

TIROS-N UNITEC STATES NOAA-NESS UNDERSTY GEOCENTRIC TIROS-N APPROVED 334 NESS STAFF ADVANCED VERY HIGH RESOLUTION TIROS-N-01 334 RACIOMETER (AVhRR) NESS STAFF TIPCS OPERATIONAL VERTICAL SOUNDER TIROS-N-02 335 (TOVS) UNKNOWN DATA COLLECTICO AND PLATFCRM LOCATION TIROS-N-03 335 SYSTEM (DCS)

TOS-F SEE ESSA e

UHURU I SEE SAS-A

UK 5 UNITED KINGDOM SRC 08/00/74 GECCENTRIC UK-5 APPROVED 336 UNITEC STATES NASA-CSS BOYD 0.3- TO 30-KEV CCSMIC X RAY WITH A UK-5 -01 336 ROTATION COLLIMATOR BOYD HIGH RESCLUTICON SOURCE SPECTRA UK-5 -03 337 ELLIOTT HIGH-ENERGY COSMIC X-RAY SPECTRA UK-5 -C5 338 -HOLT ALL-SKY MONITCR UK-5 -06 339 POUNDS 2- TO 10-KEV SKY SURVEY UK-S -02 337 POUNDS POLARIMETER/SPECTRCMETER UK-5 -04 338

UNITED KINGDOM 5 SEE UK 5

VELA 5A UNITED STATES DOD-LSAF 05/23/69 GEOCENTRIC 69-0460 05/23/69 NORMAL STO 32 SAME NEUTRON DETECTOR 69-0460-07 C5/23/69 NORMAL STD 33 KLEBESADEL GAMMA-RAY ASTRONOMY 69-04b0-08 05/23/69 NORMAL STD 33

VELA 5A (USAF) SEE VELA 5A

VELA 5B UNITED STATES DOD-LSAF 05/23/69 GEOCENTRIC 69-046E 05/23/69 NORMAL STD 33 BAME SOLAR WIND EXPERIMENT 69-046E-05 01/00/74 PARTIAL SUBS 36 SAME NEUTRON DETECTOR 69-046E-C7 05/23/69 NORMAL STD 37 CHAMBERS SOLAR X-RAY DETECTORS. 0.5 TO 3.0 A. 69-046E-C2 C1/00/74 INOPERABLE ZERO 34 1 TO 8 A. I TC 16 A. 44 TC 60 A CONNER COSMIC RAYS 69-046E-06 01/00/74 NORMAL SUBS 36 SINGER SOLAR PARTICLE TELESCOPES 69-046E-03 05/23/69 NORMAL STD 35 SINGER ELECTRON DETECTCORS 69-046C-04 05/23/69 NORMAL STD 35

VELA 5B (USAF) SEE VELA SE

1114 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES ANO PRINCIPAL INVESTIGATOR

* LAUNCH ------CURRENT STATE------* SPACECRAFT NAME CCUNTRY AND AGENCY DATE ORBIT TYPE **~~~~************************** * *******NSSOC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

VELA 6A UNITED STATES DOO-SAF 04/08/70 GEOCENTRIC 70-027A 04/08/70 NORMAL STD 47 BAME SOLAR WIND EXPERIMENT 70-027A-05 04/12/72 PARTIAL SUBS 49 UAME NEUTRON DETECTCR 70-027A-07 04/08/70 NORMAL STD 50 CHAMBERS SOLAR X-RAY DETECTORS. 0.5 TO 3.0 A, 70-027A-02 04/08/70 NORMAL STD 48 1 TO 8 A, 1 TO 16 A, 44 TO 60 A KLEBESADEL GAMMA-RAY ASTRONOMY 70-027A-08 04/08/70 NORMAL STD 50 SINGER SOLAR PARTICLE TELESCOPES 70-027A-03 04/08/70 NORMAL STD 48 SINGER ELECTRON DETECTORS 70-027A-04 04/08/70 NORMAL STD 49

VELA 6A (USAF) SEE VELA 6A

VELA 68 UNITED STATES DOD-LSAF 04/08/70 GEOCENTRIC 70-0278 04/08/70 NORMAL STD 51 SAME NEUTRON DETECTOR 70-0278-07 04/08/70 NORMAL STD 53 CHAMBERS SOLAR X-RAY DETECTORS, 0.5 TO 3.0 A. 70-0278-02 04/08/70 NORMAL STD 51 1 TO 8 A. 1 TO 16 A. 44 TO 60 A KLEBESADEL GAMMA-RAY ASTRChCMY 70-0278-08 04/08/70 NORMAL STD 53 SINGER SOLAR PARTICLE TELESCOPES 70-0278-03 04/08/70 NORMAL STD 52 SINGER ELECTRON DETECTORS 70-0278-04 04/08/70 NORMAL STO 52

VELA 68 (USAF) SEE VELA 68

VELA 9 (TRW) SEE VELA EA

VELA 10 (TRW) SEE VELA 56

VELA 11 (TRW) SEE VELA 6A

VELA 12 (TRw) SEE VELA 6E

VIKING-A LANDER UNITED STATES NASA-OSS 3 QTR 75 MARS LANCER VIKG-AL APPROVED 1065 ANDERSON SEISMOLOGY VIKG-AL-08 1065 BIEMANN MCLECULAR ANALYSIS VIKG-AL-04 1066 HARGRAVES MAGNETIC PROPERTIES VIKG-AL-10 1066 HESS METEOROLOGY EXPERIMENT VIKG-AL-07 1067 KLEIN BIOLOGY INVESTIGATION VIKG-AL-03 1067 MICHAEL. JR. RADIO SCIENCE VIKG-AL-11 1067 MUTCH FACSIMILE CAMERA VIKG-AL-06 1068 NIER ENTRY-ATMOSPhERIC STRUCTURE VIKG-AL-02 1068 NIER ENTRY-ATMOSPHERIC COMPOSITION VIKG-AL-12 106g SHURTHILL PHYSICAL PROPERTIES INVESTIGATION VIKG-AL-01 1070 TOULMIN. III X-RAY FLOURESCENCE SPECTROMETER VIKG-AL-13 1070

1071 VIKING-A ORBITER UNITED STATES NASA-OSS 3 QTR 75 MARSCENTRIC VIKG-A APPROVED CARR URBITER IMAGING VIKG-A -01 1071 FARMER IR SPECTROMETER -- WATER VAPCR MAPPING VIKG-A -03 1072 KIEFFER IR RADICMETRY -- THERMAL MAPPING VIKG-A -02 1072

1073 VIKING-B LANDER UNITED STATES NASA-CSS 3 OTR 75 MARS LANCER VIKG-BL APPROVED

1115 CUMULATIVE INDEX OF ACTIVE AND PLANNED SPACECRAFT AND EXPERIMENTS BY SPACECRAFT NAMES AND PRINCIPAL INVESTIGATOR

LAUNCH * ------CURRENT STATE------* SPACECRAFT NAME COUNTRY AND AGENCY DATE ORBIT TYPE **~~~~********************* ************ NSSDC ID EPOCH STATUS DATA PAGE *PRINC.INVEST.NAME EXPERIMENT NAME * MMDDYY RATE NO.

ANDERSON SEISMOLOGY VIKG-BL-08 BIEMANN 1073 MOLECULAR ANALYSIS VIKG-BL-04 1074 HANGRAVES MAGNETIC PROPERTIES V[KG-BL-10 1075 HESS METEOROLOGY EXPERIMENT VIKG-BL-07 1075 KLEIN BIOLOGY INVESTIGATION VIKG-BL-03 1075 MICHAEL. JR. RADIO SCIENCE VIKG-BL-11 1076 MUTCH FACSIMILE CAMERA VIKG-BL-06 1076 NIER ENTRY-ATMOSPHERIC STRUCTURE VIKG-BL-02 1077 NIER ENTRY-ATMOSPHERIC COMPOSITION VIKG-BL-12 1077 SHURTHILL PHYSICAL PROPERTIES INVESTIGATICN VIKG-BL-01 1078 TOULMIN. III X-RAY FLOURESCENCE SPECTROMETER VIKG-BL-13 1078

VIKING-B ORBITER UNITED STATES NASA-CSS 3 QTR 75 MARSCENTFIC VIKG-8 APPROVED 1079 CARR ORBITER IMAGING VIKG-B -01 FARMER 1080 IR SPECTROMETER -- WATER VAPOR MAPPING VIKG-B -03 1080 KIEFFER IR RADIOMETRY -- THERMAL MAPPING VIKG-B -02 1081

1116 SECTION 2.2 - CUMULATIVE BAR GRAPH INDEXES FOR ELECTROMAGNETIC RADIATION EXPERIMENTS

As discussed in some detail in the original report, the NSSDC information system permits the generation of bar graphs illustrating when instruments sensing various phenomena were operational. Several such graphs illustrating not only magnetic and electric field coverage but also charged particle coverage, grouped by energy and region of measurement, were printed in the original report. A new set of bar graphs has recently been generated covering electromagnetic radiation from solar and non-solar sources separately for experiments with limited spectral resolution (X/AX < 10) and jointly for experiments with greater spectral resolution (X/AX > 10). These bar graphs are included in the following pages. In the future it is planned to include a full set of bar graphs in the annual report only. 50LA lOADIBAiOILICTODMASIIETIC AOIATION 3/31/14 MSSOC, GREENBELT MD.

101*

ISIS 1 (10) 3.0113/1.5 311 ------* ------

"9 |NIM)US 9 (1) 3.313/1.1E3 r -'------50LR*D 10 (1) 1.613/7. E-2 B -- r r----;~- SOLRAD 1i (8) 1.3E3/1.1E3

S-*...... *...... 50LA3 IA (8) 1.3131.1E3 3

E'C.AE-C (51 (5) 1.2E3/.9,EI w I .9

1*-Cf (S3 5.Z13/4.13SOL AD ] A (7) 1.0E3/I1.E2 101

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10 -

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.3 IMP-i (A) 1. l ACE SOLOAD 11 (5) 1.60E/.0EO I

SSOLRAD IA (11) .00/ .0E0 ***************************w.

- I . 50L0D 3 (0) 2.10/2.5EO 5"-o..O :.0p..5*...... :. :....0)...... 1 SOLSAD-33Ai(30).2.220/2.C 10 I SOLIAD 3i (l) 5.3 1E.OEO

S I...... *+**....oe..H...

SOLIRAO 118 (1) 0.3E-1/8.3E-2

-0L AD IA (10 ). E~/ . 3E-2

10SOLID I (1) .01 .0-

S69 70 71 72 73 74 75 76 .77 8 79 80 EXPERIMENT OPERATIONAL HISTORY (YEARS) ASTROORICAL BROADBAND ELECTRORAMMETIC 0AD11TION 3/31/T% NSSOC, Slt(IULI tD. 10 Tfynl- l- fif itliTtt li llI liIEgIEW IVg1111 I111grw1Ei ollml 11 oEwElEl EEE E 11 Ei ElwIIIIIJIEEIIEu IfI 10

PIONEER VENUS PRO[E E (2) 9.01319.0E3 PIONEER VENUS P009E D 12) 9.03/9.03

PIONEER VENUS PROOE C (2) 9.0(3/9.013 *******************************W PIONEER VENUS PPOI 9 (t) 9.0/319.0E3 1.... *...... PIONEER 1 1 ) 7).0E3/3.9E3 9 PIONEER 10 (7) .0E3/3.9E3 C) TO IA (I~ 2.T13/I.3E3 9 S-- -*-*-*------2 0 SiSOLOD Ill (19) 1.9E3/2. E2 I I*.*....*.*...... ' ...... '. SOLAD IIA (191 (.9(3/2.0E2 1 (6)) 0 0 11PONEER(1 1..OE23/2..0E2 10I S4L:D 110(l)l 932.0(3 - 0Pl0EER 11 (6) 0 .0E2/2.0E2 PIOEER 10 (6) 0.0(2/2.0(2

ASTP (2) 3.0E213.0E2 - 10' I...... 1l- 0' Lur 040-3 (2) 6.0EI/3.0E0 ,I s

SOLROA IIS (29) 2 51/6.2E-1

IP-J1.61/1.0 (01 ...... i o-. IP-J ( ) I.6EI/1.EO-D

-H 16E

VE OLRD 16) EO1-2OE.3E-3

VELA S0 (0 6.2E-2/ 1.21-2

IV(LA 66 (8) 9.lE-2/8.3E-3

TO 10 (5 2.5E-4./2.E-5.

lo-10, I.....r------10'

69 70 71 72 T3 T7 75 76 77 78 79 80 EXPERIAENT OPERATIONAL HISTORY (YEARS) SPECTRAL MEASURMENTS (ALL SOLAR, EICEPT 0*0-3) 3131/7 NSSOC, E0ISSIELT R. ggggggg ggg IIII5 ggggggllIIIIIl Igil IluIIIIIII I lll III IIi Il I

aII I

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a I 10 -

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i I S

OAO 3 (I) 3.312/1.IE2 r -I

10 T2 3 74 7I 76 TT EXPERIMENT OPERATIONAL HISTORY (YEARS) EXPERIET OPERIONAL HlISTOIRY (YEARS) SECTION 3 - SPACECRAFT AND EXPERIMENTS LAUNCHED OR INACTIVATED BETWEEN APRIL 1, 1973, AND MARCI 31, 1974

Title Page

3.1 Spacecraft Launched ...... 1125 3.2 Spacecraft and Experiments Which Became Operational Off ...... 1133 3.3 Spacecraft and Experiments Which Became Inoperable ...... 1137

1123 Spacecraft Launched SECTION 3.1 - SPACECRAFT LAUNCHED

The following table of spacecraft successfully launched between April 1, 1973, and March 31, 1974, consists of both active spacecraft and other spacecraft for which little is known beyond the fact that they have been launched and have the initial orbit parameters indicated. This second group is included to inform the scientific community of the spacecraft launching; it is anticipated that such information may be relevant to studies performed by the users of this document. Some information concerning these lesser known spacecraft is available. through the SPACEWARN Bulletin (described in the Introduction to the annual report).

This table is ordered chronologically by the spacecraft launch date. The spacecraft common name, NSSDC ID code, spacecraft funding country/ countries, orbit type, and spacecraft orbit parameters (epoch date, apoapsis, periapsis, inclination, and period) are also included for each spacecraft entry listed in the table. The distance and time parameters are shown in km altitude and minutes except for heliocentric-type orbits, where they are shown in AU radial and days.

li25 SPACECRAFT LAUNCHED

PERIOD SPACECRAFT NAME NSSDC 1) FUNDING CCUNTRY LAUNCH DATE EPOCH DATE ORBIT TYPE APOAPSIS PERIAPSIS INCLINATION

SALUTE 2 73-017A U.S.S.R. 04/04/73 04/04/73 GEOCENTRIC 260.0 215.0 51.6 89.0

11.4 MOLNIYA 2E 73-018A U.S.S.R. 04/05/73 04/06/73 GEOCENTRIC 39100.0 500.0 65.0

PIONEER 11 73-019A UNITED STATES 04/06/73 JUPITER FLYRY

COSMOS 553 73-020A U.S.S.R. 04/12/73 04/13/73 GEOCENTRIC 519.0 282.0 71.0 92.2

89.5 COSMOS 554 73-021A U.S.S.R. 04/19/73 04/20/73 GEOCENTRIC 308.0 212.0 72.9

INTERCOSMOS 9 73-022A U.S.S.R. 04/19/73 04/2C/73 GEOCENTRIC 1552.0 202.0 48.5 102.2

ANIK 2 73-023A CANADA 04/19/73 05/01/73 GEOCENTRIC 35788.0 35781.0 0.1 1436.0

COSMOS 555 73-024A U.S.S.R. 04/25/73 04/26/73 GEOCENTRIC 253.0 216.0 81.3 89.0

COSMOS 556 73-025A U.S.S.R. 05/05/73 05/06/73 GEOCENTRIC 252.0 209.0 81.3 89.0

CUSMOS 557 73-026A U.S.S.R. 05/11/73 05/12/73 GEOCENTRIC 266.0 218.0 51.6 89.1

93.4 SKYLAB 73-027A UNITED STATES 05/14/73 05/14/73 GEOCENTRIC 442.0 434.C 50.0

89.9 1973-028A 73-028A UNITED STATES 05/16/73 05/17/73 GEOCENTRIC 399.0 139.0 110.5

71.0 92.3 COSMOS 558 73-029A U.S.S.R. 05/17/73 05/17/73 GEOCENTRIC 501.0 269.C

65.4 89.8 COSMOS 559 73-030A U.S.S.R. 05/18/73 05/19/73 GEOCENTRIC 345.0 217.0

72.9 89.7 COSMOS 560 73-031A U.S.S.R. 05/23/73 05/24/73 GEOCENTRIC 336.0 211.0

50.0 93.2 SKYLAB CSM 1 73-032A UNITED STATES 05/25/73 05/25/73 GEOCENTRIC 438.0 428.0

65.4 89.5 COSMOS 561 73-033A U.S.S.R. 05/25/73 05/26/73 GEOCENTRIC 317.0 215.0

81.2 102.5 METEOR 15 73-034A U.S.S.R. 05/29/73 05/30/73 GEOCENTRIC 909.0 867.C

71.0 92.1 COSMOS 562 73-035A U.S.S.R. 06/05/73 06/06/73 GEOCENTRIC 510.0 282.C

65.4 89.5 COSMOS 563 73-036A U.S.S.R. 06/06/73 06/07/73 GEOCENTRIC 320.0 312.0

74.0 114.5 COSMOS 564 73-037A U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0 1392.0

74.0 114.5 COSMOS 565 73-0378 U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0 1392.0

114.5 COSMOS 566 73-037C U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0 1392.0 74.0

74.0 114.5 COSMOS 567 73-0370 U.SIS.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0 1392.0

1392.0 74.0 114.5 COSMOS 568 73-037E U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0

1392.0 74.0 11445 COSMOS 569 73-037F U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0

74.0 114.5 COSMOS 570 73-037G U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0 1392.0

1392.0 74.0 114.5 COSMOS 571 73-037H U.S.S.R. 06/08/73 06/09/73 GEOCENTRIC 1507.0 .

T PRECEDING PAGE BLAN K NOT FEMM 1127 SPACECRAFT LAUNCHED

SPACECRAFT NAME NSSDC ID FUNDING COUNTRY LAUNCH DATE EPOCH DATE ORBIT TYPE APOAPSIS PERIAPSIS INCLINATION PTRIOD

COSMOS 572 73-038A U.S.S.R. 06/10/73 06/11/73 GEOCENTRIC 294.0 211.0 51.7 89.3

RAE-B 73-039A UNITED STATES 06/10/73 09/07/73 GEOCENTRIC 1070.3 1059.1 38.7 221.9

1973-040A 73-040A UNITED STATES 06/12/73 07/01/73 GEOCENTRIC 35901.0 35533.C 0.5 1431.9

COSMOS 573 73-041A U.S.S.R. 06/15/73 06/16/73 GEOCENTRIC 329.2 196.2 51.6 Eg9.

COSMOS 574 73-042A U.S.S.R. 06/20/73 06/21/73 GEOCENTRIC 1026.0 996.0 83.0 105.0

COSMOS 575 73-043A U.S.S.R. 06/21/73 06/22/73 GEOCENTRIC 299.0 208C.C 65.4 89.3

COSMOS 576 73-044A U.S.S.R. 06/27/73 06/28/73 GEOCENTRIC 356.0 212.' 72.9 89.9

MOLNIYA 2F 73-045A U.S.S.R. 07/11/73 07/12/73 GEOCENTRIC 39280.0 480.0 65.3 7C5. 0

1973-046A 73-046A UNITED STATES 07/13/73 07/15/73 GEOCENTRIC 269.0 156.0 96.2 88.8

MARS 4 73-047A U.S.S.R. 07/21/73 MARS FLYBY

COSMOS 577 73-048A U.S.S.R. 07/25/73 07/26/73 GEOCENTRIC 312.0 209.C 65.4 89.5

MARS 5 73-049A U.S.S.R. 07/25/73 MARS FLYBY

SKYLAB CSM 2 73-050A UNITED STATES 07/28/73 07/28/73 GEOCENTRIC 441.0 423.0 53.0 93.2

COSMOS 578 73-051A U.S.S.R. 08/01/73 08/02/73 GEOCENTRIC 308.0 207.0 65.4 89.4

MARS 6 73-052A U.S.S.R. 08/05/73 MARS LANDER

MARS 7 73-053A U.S.S.R. 08/09/73 MARS FLYBY

1973-054A 73-054A UNITED STATES 08/17/73 08/17/73 GEOCENTRIC 852.0 811.0 98.9 101.6

COSMOS 579 73-055A U.S.S.R. 08/21/73 08/22/73 GEOCENTRIC 315.0 209.0 65.4 89.5

1973-056A 73-056A UNITED STATES 08/21/73 09/01/73 GEOCENTRIC 39296.0 461.0 63.3 705.7

COSMOS 580 73-057A U.S.S.R. 08/22/73 08/23/73 GEOCENTRIC 518.0 283.0 71.0 92.2

INTELSAT 4 F-7 73-058A UNITED STATES 08/23/73 10/01/73 GEOCENTRIC 35794.0 35781.0 0.4 1436.1

COSMOS 581 73-059A U.S.S.R. 08/24/73 08/25/73 GEOCENTRIC 303.0 211.0 51.6 89.4

COSMOS 582 73-060A U.S.S.R. 08/28/73 08/29/73 GEOCENTRIC 559.0 521.0 74.0 95.3

MOLNIYA 1I 73-061A U.S.S.R. 08/30/73 08/31/73 GEOCENTRIC 37970.0 480.0 65.3 619.0

COSMOS 583 73-062A U.S.S.R. 08/30/73 08/31/73 GEOCENTRIC 316.0 208.0 65.0 89.5

COSMOS 584 73-063A U.S.S.R. 09/06/73 09/07/73 GEOCENTRIC 360.0 213.0 72.9 89.9

COSMOS 585 73-064A U.S.S.R. 09/08/73 09/09/73 GEOCENTRIC 1416.0 1385.C 74.0 113.6

1128 SPACECRAFT LAUNCHED

INCLINATION PERICD LAUNCH DATE EPOCH DATE ORBIT TYPE APOAPSIS PERIAPSIS SPACECRAFT NAME NSSDC D10FUNDING CCUNTRY 83.0 IC5.0 09/14/73 09/15/73 GEOCENTRIC 1020.0 986.0 COSMOS 586 73-065A U.S.S.R. 65.4 89.6 09/21/73 09/22/73 GEOCENTRIC 330.0 215.0 COSMOS 587 73-066A U.S.S.R. 51.6 88.6 09/27/73 09/28/73 GEOCENTRIC 249.0 194.0 SOYUZ 12 73-067A U.S.S.R. 110.5 89.7 09/27/73 09/28/73 GEOCENTRIC 385.0 131.C 1973-068A 73-068A UNITED STATES 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.0 COSMOS 588 73-069A U.S.S.R. 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.0 COSMOS 589 73-0698 U.S.S.R. 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.0 COSMOS 590 73-069C U.S.S.R. 204.0 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 COSMOS 591 73-0690 U.S.S.R. 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.0 COSMOS 592 73-069E U.S.S.R. 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.0 COSMOS 593 73-069F U.S.S.R. 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.C COSMOS 594 73-069G U.S.S.R. 72.8 89.7 10/02/73 10/03/73 GEOCENTRIC 312.0 204.C COSMOS 595 73-069H U.S.S.R. 72.8 89.7 10/03/73 10/04/73 GEOCENTRIC 312.0 204.0 COSMOS 596 73-070A U.S.S.R. 65.4 89.5 10/06/73 10/07/73 GEOCENTRIC 312.0 212.0 COSMOS 597 73-071A U.S.S.R. 72.9 90.0 10/10/73 10/11/73 GEOCENTRIC 360.0 213.0 COSMOS 598 73-072A U.S.S.R. 206.C 65.0 89.3 10/15/73 10/16/73 GEOCENTRIC 294.0 COSMOS 599 73-073A U.S.S.R. 72.9 90.0 10/16/73 10/17/73 GEOCENTRIC 366.0 215.0 COSMOS 600 73-074A U.S.S.R. 82.0 1C2.3 10/16/73 11/17/73 GEOCENTRIC 1561.0 210.0 COSMOS 601 73-075A U.S.S.R. 62.8 736.0 10/19/73 10/20/73 GEOCENTRIC 40600.0 509.0 MOLNIYA 2G 73-076A U.S.S.R. 72.9 90.0 10/20/73 10/21/73 GEOCENTRIC 365.0 213.0 COSMOS 602 73-077A U.S.S.R. 28.7 17279.0 10/26/73 10/29/73 GEOCENTRIC 288857.0 141185.0 IMP-J 73-078A UNITED STATES 72.9 90.1 10/27/73 10/28/73 GEOCENTRIC 380.0 213.5 COSMOS 603 73-079A U.S.S.R. 81.2 97.2 10/29/73 10/30/73 GEOCENTRIC 647.0 624.C COSMOS 604 73-080A U.S.S.R. 90.2 106.0 10/31/73 10/31/73 GEOCENTRIC 1139.0 902.0 OSCAR(NAV) 20 73-081A U.S.S.R. 74.0 1C2.0 10/30/73 10/31/73 GEOCENTRIC 1477.0 265.0 INTERCOSMOS 10 73-082A U.S.S.R. 62.8 90.7 10/31/73 11/01/73 GEOCENTRIC 424.0 221.0 COSMOS 605 73-083A U.S.S.R. 657.0 (2.9 709.9 11/02/73 11/03/73 GEOCENTRIC 39310.0 COSMOS 606 73-084A U.S.S.R.

11/03/73 VENUS FLYBY MARINER 10 73-085A UNITED STATES

1129 SPACECRAFT LAUNCHED

SPACECRAFT NAME NSSDC ID FUNDING CCUNTRY LAUNCH DATE EPOCH DATE ORBIT T-YPE APOAPSIS PERIAPSIS INCLINATION PERIOD

NUAA 3 73-086A UNITED STATES 11/06/73 11/07/73 GEOCENTRIC 1509.2 1500.0 102.1 116.1

COSMOS 607 73-087A U.S.S.R. 11/10/73 11/11/73 GEOCENTRIC 364.0 214.0 72.9 90.0

1973-088A 73-088A UNITED STATES 11/10/73 11/11/73 GEOCENTRIC 275.0 159.0 96.9 88.9

1973-0888 73-0888 UNITED STATES 11/10/73 11/11/73 GEOCENTRIC 257.0 159.C 96.9 88.7

1973-0880 73-0880 UNITED STATES -11/10/73 11/11/73 GEOCENTRIC 508.0 486.0 96.3 94.6

MOLNIYA 1ZA 73-089A U.S.S.R. 11/14/73 11/15/73 GEOCENTRIC 39197.0 480.0 65.0 7C2.0

,KYLAB CSM-3 73-090A UNITED STATES 11/16/73 11/17/73 GEOCENTRIC 435.0 435.0 50,0 90.0

COSMOS bC8 73-091A U.S.S.R. 11/20/73 11/21/73 GEOCENTRIC 528.0 281.0 71.0 53.2

COSMOS 609 73-092A U.S.S.R. 11/21/73 11/22/73 GEOCENTRIC 370.0 207.0 70.0 90.0

COSMOS 610 73-093A U.S.S.R. 11/27/73 11/28/73 GEOCENTRIC 560.0 515.0 74.0 95.2

COSMOS 611 73-094A U.S.S.R. 11/28/73 11/30/73 GEOCENTRIC 481.0 270.0 71.0 92.1

COSMOS 612 73-095A U.S.S.R. 11/28/73 11/29/73 GEOCENTRIC 371.0 214.0 72.9 90.1

COSMOS 613 73-096A U.S.S.R. 11/30/73 12/01/73 GEOCENTRIC 295.0 195.0 51.6 E9.1

MOLNIYA IZO 73-097A U.S.S.R. 11/30/73 12/01/73 GEOCENTRIC 40829.0 460.0 62.7 737.0

COSMOS 614 73-098A U.S.S.R. 12/04/73 12/05/73 GEOCENTRIC 830.0 770.0 74.0 100.7

COSMOS 615 73-099A U.S.S.R. 12/13/73 12/14/73 GEOCENTRIC 859.0 280.0 71.0 55.7

1973-IOOA 73-100A UNITED STATES 12/13/73 01/05/74 GEOCENTRIC 36475.0 35065.0 2.7 1435.2

1973-100 73-1008 UNITED STATES 12/13/73 01/07/74 GEOCENTRIC 36299.0 35349.C 2.3 1438.0

AE-C 73-101A UNITED STATES 12/16/73 12/17/73 GEOCENTRIC 4303.0 158.0 68.1 132.5

COSMOS 616 73-102A U.S.S.R. 12/17/73 12/18/73 GEOCENTRIC 355.0 214.0 72.9 89.9

SOYUZ 13 73-103A U.S.S.R. 12/18/73 12/19/73 GEOCENTRIC 272.0 225.0 51.6 E9.2

COSMOS 617 73-104A U.S.S.R. 12/19/73 12/26/73 GEOCENTRIC 1486.0 1336.0 74.0 114.0

COSMOS 618 73-1048 U.S.S.R. 12/19/73 12/20/73 GEOCENTRIC 1489.0 1446.0 74.0 115.3

COSMOS 619 73-104C U.S.S.R. 12/19/73 12/20/73 GEOCENTRIC 1493.0 1423.0 74.0 115.1

COSMOS 62C 73-104D U.S.S.R. 12/19/73 12/21/73 GEOCENTRIC 1495.0 1461.0 74.0 115.5

COSMOS 621 73-104E U.S.S.R. 12/19/73 12/20/73 GEOCENTRIC 1485.0 1410.0 74.0 114.8

COSMOS 622 73-104F U.S.S.R. 12/19/73 12/20/73 GEOCENTRIC 1487.0 1371.0 74.0 114.4

1130 SPACECRAFT LAUNCHED

INCLINATION PERIOD SPACECRAFT NAMb NSSDC ID FUNDING CCUNTRY LAUNCH DATE EPOCH DATE ORBIT TYPE APOAPSIS PERIAPSIS

114.6 COSMOS 623 73-104G U.S.S.R. 12/19/73 12/20/73 GEOCENTRIC 1487.0 1389.0 74.0

74.0 114.2 COSMOS 624 73-104- U.S.S.R. 12/19/73 12/20/73 GEOCENTRIC 1474.0 1366.0

214.0 72.8 89.8 COSMOS 625 73-105A U.S.S.R. 12/21/73 12/22/73 GEOCENTRIC 346.0

488.0 62.9 737.0 MOLNIYA 2H 73-106A U.S.S.R. 12/25/73 12/26/73 GEOCENTRIC 40809.0

407.0 74.0 109.2 UREOL 2 73-107A U.S.S.R. 12/26/73 12/27/73 GEOCENTRIC 1995.0

65.0 89.7 COSMOS 626 73-108A U.S.S.R. 12/27/73 12/29/73 GEOCENTRIC 259.0 257.0

83.3 105.1 COSMOS 627 73-109A U.S.S.R. 12/29/73 12/30/73 GEOCENTRIC 1019.0 974.0

975.0 83.0 105.0 COSMOS 628 74-001A U.S.S.R. 01/17/74 01/18/74 GEOCENTRIC 1026.0

37.6 121.5 SKYNET 2A 74-002A UNITED KINGDOM 07/00/73 01/20/74 GEOCENTRIC 3406.0 96.0

202.0 62.8 89.4 COSMOS 629 74-003A U.S.S.R. 01/24/74 01/25/74 GEOCENTRIC 315.0

213.0 72.9 90.0 COSMOS 630 74-004A U.S.S.R. 01/30/74 01/31/74 GEOCENTRIC 367.0

522.C 74.0 95.3 COSMOS 631 74-0054 U.S.S.R. 02/06/74 02/07/74 GEOCENTRIC 565.0

333.0 184.0 65.0 89.4 COSMOS 632 74-006A U.S.S.R. 02/12/74 02/13/74 GEOCENTRIC

134.0 110.4 89.8 1974-007A 74-007A UNITED STATES 02/13/74 02/15/74 GEOCENTRIC 393.0

288.0 31.2 121.8 TANSEI-II 74-008A JAPAN 02/16/74 02/17/74 GEOCENTRIC 3238.0

2.9 95.9 SAN MARCO 4 74-009A UNITED STATES 02/18/74 02/22/74 GEOCENTRIC 910.0 231.0 ITALY

280.0 71.0 92.2 COSMOS 633 74-010A U.S.S.R. 02/27/74 02/27/74 GEOCENTRIC 516.0

832.0 81.2 102.2 METEOR 16 74-011A U.S.S.R. 03/05/74 03/09/74 GEOCENTRIC 894.0

271.0 70.9 92.2 COSMOS 634 74-012A U.S.S.R. 03/05/74 03/07/74 GEOCENTRIC 491.0

714.0 97.8 101.2 X-4 74-013A UNITED KINGDOM 03/08/74 03/13/74 GEOCENTRIC 916.0

COSMOS 635 74-014A U.S.S.R. 03/14/74 03/15/74 GEOCENTRIC 350.0 212.0 72.9 89.8

98.9 1C1.5 1974-015A 74-015A UNITED STATES 03/16/74 33/16/74 GEOCENTRIC 877.0 782.0

COSMOS 636 74-016A U.S.S.R. 03/20/74 03/21/74 GEOCENTRIC 409.0 174.0 65.0 90.0

COSMOS 637 74-017A U.S.S.R. 03/26/74 03/26/74 GEOCENTRIC 230.0 178.0 51.5 88.5

1131 Spacecraft and Experiments Which Became Operational Off SECTION 3.2 - SPACECRAFT AND EXPERIMENTS WHICH BECAME OPERATIONAL OFF

The following table identifies spacecraft and/or experiments placed in an operational off status between April 1, 1973, and March 31, 1974. The table is ordered alphabetically by spacecraft common name. For each spacecraft listed, the following information appears: the spacecraft common name, the NSSDC ID code, the spacecraft funding country/countries, the launch date, the date the spacecraft was placed in an operational off mode, the orbit type, and the spacecraft orbit parameters (epoch date, apoapsis, periapsis, inclination, and period). The distance and time parameters are shown in km altitude and minutes except for heliocentric-type orbits, where they are shown in AU radial and days.

Operational off experiments are listed immediately below their associated spacecraft entry. The experiment NSSDC ID code, the experimenter's last name, the NSSDC experiment name, and the date the experiment was placed in an operational off mode are given for each experiment. To indicate that a spacecraft was not placed in an operational off mode, even though some of its experiments were in such a mode, the column indicating spacecraft operational off mode date will appear blank.

1133 SPACECRAFT AND EXPERIMENTS %HICH BECAME OPERATIONAL OFF

* LAUNCH DATE S/C EPOCH URBIT TYPE APO- PERI- INCLI- *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY DATE PLACED DATE APSIS APSIS NATION PERIOD * OP OFF 4 4 * 4 * * *44 * * * * * * *4***4*4* 4** * * ** * * * * **4* 4* 44 4 DATE EXP * 4 EXPERIMENTER EXPERIMENT NAME PLACED * * OP OFF *

ALOUETTE 2 65-098A CANADA 11/29/65 06/03/73 01/24/72 GEOCENTRIC 2935.0 510.0 79.8 120.9 UNITED STATES 65-098A-01 WHITTEKER SWEEP FREQUENCY SOUNDER 06/03/73 65-098A-C2 BELROSE VLF RECEIVER 06/03/73 65-098A-'3 HAETZ COSMIC RADIO NOISE 06/03/73 65-98A-04 MCDIARMID ENERGETIC PARTICLES DETECTORS 06/03/73 65-09A-5 BRACE CYLINDRICAL ELECTROSTATIC PROBE 06/03/73

ATS 5 69-069A UNITED STATES 08/12/69 / / 08/23/69 GEOCENTRIC 36894.0 35760.0 2.6 1463.0 69-C69A-)4 MOZER TRI-DIRECTIONAL MEDIUM-ENERGY PARTICLE 09/01/73 DETECTOR

NIMBUS 4 7 ?-025A UNITED STATES 04/08/70 / / 09/07/73 GEOCENTRIC 1099.3 1087.5 99.8 107.1 70--25SA-10 HOUGHTON SELECTIVE CHOPPER RADIOMETER (SCR) 06/00/73

PIONEER 11 73-019A UNITED STATES 04/06/73 / / JUPITER FLY 73-?19A-08 MUNCH INFRARED RADIOMETER 34/06/73

SKYLAB 73-027A UNITED STATES 05/14/73 09/25/73 05/14/73 GEOCENTRIC 442.0 434.0 50.0 93.4 73-027A-01 SHAPIRO NUCLEAR EMULSION 09/25/73 73-027A-02 HENIZE ULTRAVIOLET STELLAR ASTRONOMY 09/25/73 73-C27A-13 TOUSEY UV/X-RAY SOLAR PHOTOGRAPHY 09/25/73 73-027A-07 MILLIGAN DUAL X-RAY TELESCOPE 09/25/73 73-027A-C8 PACKER UV AIRGLOW HORIZON PHCTOGRAPHY 09/25/73 73-?7A-G9 WEINbERG GEGENSCHEIN/ZODIACAL LIGHT 09/25/73 73-027A-10 TOUSEY UV CORCNAL SPECTROnELICGRAPH 09/25/73 73-027A-11 TOUSEY EUV SPECTROGRAPH 09/25/73 73-027A-12 HEMENAAY PARTICLE CCLLECTION 09/25/73 73-027A-14 COURTES ULTRAVIOLET PANORAMA 09/25/73 73- 27A-15 PEEVES HYDROGEN ALPHA TELESCOPE NUMBER 1 09/25/73 73-127A-16 UNKNOWN HYDROGEN ALPHA TELESCCPE NUMBER 2 09/25/73 73-f327A-17 DEMEL MULTISPECTRAL PHOTOGRAPHY FACILITY 09/25/73 73-027A-18 BARNETT INFRARED SPECTROMETER 09/25/73 73-021A-19 KORS MULTISPECTRAL SCANNER 09/25/73 73-027A-2C EVANS MICROWAVE RACIOMETER/SCATTEROMETER/ 09/25/73 ALTIMETER 73-027A-21 EVANS L-eAND MICROWAVE RADICMETER 09/25/73 73-C27A-22 FORBES EXPANDABLE AIRLOCK MECHANISM 09/25/73 73-027A-23 LEHN THERMAL COATINGS 09/25/73 73-027A-24 WHEDON MINERAL EALANCE 09/25/73 73-027A-25 LEACH BID-ASSAY CF BODY FLUIDS 09/25/73 7-0127A-26 ORD SPECIMEN MASS MEASUREMENT 09/25/73 73-027A-27 ALLEBACH VECTOR CARDICGRAM 09/25/73 73-C27A-28 6RAYDIEL HUMAN VESTIBULAR FUNCTION 09/25/73 7s-r27A-29 FROST SLEEP MONITOR 09/25/73 73-%P7A-3C KUBIS TIWE AND MCTICN STUDY 09/25/73 pRECETG .ACE BL2ANK NOT F7LMED 1135 SPACECRAFT AND EXPERIMENTS WHICH BECAME OPERATIONAL OFF

* LAUNCH DATE S/C EPOCH ORUIT TYPE APO- PERI- INCLI- 4SPACECRAFT NAMF NSSDC 10 FUNDING COUNTRY DATE PLACED DATE APSIS APSIS NATION PERIOD * CP OFF

SDATE EXP * * EXPERIMENTER ExPERI ENT NAME PLACED * *OP OFF *

73-027A-31 MICHEL METABOLIC ACTIVITY 09/25/73 73-,27A-32 THORNTON BODY MASS MEASUREMENT 09/25/73 73-n27A-33 MC KANNAN THERMAL CONTRCL COATINGS 09/25/73 73-027A-34 KIMZFY ZERO GRAVITY FLAMMABILITY 09/25/73 73-C27A-35 JOHNSCN, JR. HABITAEILITY/CREW QUARTERS 09/25/73 73-'27A-36 RENDALL GRAVITY WORKBENCH 09/25/73 73-027A-37 JACKSCN EVA/IVA HARDWAkE EVALUATION 09/25/73 73-C27A-38 WHITSETT. JR. ASTRONAUT MANEUVERING EQUIPMENT 09/25/73 73-$27A-39 POORMAN MATERIALS PROCESSING FACILITY 09/25/73 EXPERIMENTS 7--027A-4A RANDLE MANUAL NAVIGATION SIGPTINGS 09/25/73 73-n27A-41 LEAVITT IN-FLIGHT EXPERIMENT AEROSOL ANALYSIS 09/25/73 73-G27A-42 CONWAY CREW/VEHICLE DISTURBANCES 09/25/73 73-027A-43 GOULD PRECISICN OPTICAL TRACKING 09/25/73 73-027A-44 HEWES FCOT-CCNTRCLLED MANEUVERING UNIT 09/25/73 73-027A-45 GREENEERG CORONOGRAPH CONTAMINATION MEASUREMENTS 09/25/73 73-C27A-4E MUSCARI CONTAMINATIhN MEASUREMENTS 09/25/73 73-027A-47 EDWAPOS PILOT DESCRIPTION 09/25/73 73-C27A-45 PRICE TRANSURANIC COSMIC RAYS 09/25/73 73-027A-49 GCISS FOIL HEAVY NUCLEI ABUNDANCE EXPERIMENT 09/25/73 73-027A-5C VOGEL BONE MINERAL MEASUREMENT 09/25/73 73-'27A-l JOHNSON LOWER BODY NEGATIVE PRESSURE 09/25/73 73-327A-52 LOCKHART CYTCGENETIC STUDIES OF THE BLOOD 09/25/73 73-027A-53 RITZMANN MAN'S IMMUNITY - IN VITRO ASPECTS 09/25/73 73-_27A-54 JCHNSCN BLOOD VOLUME AND RED CELL LIFE SPAN 09/25/73 73-027A-55 MENGEL RED BLCCC CELL METAOOLISM 09/25/73 72-)27A-56 KIMZEY SPECIAL HEMATOLOGIC EFFECT 09/25/73 73-^27A-57 WIEDEMEIER MULTIPURPFSE ELECTRIC FURNACE 09/25/73 73-027A-5e CBND CREW ACTIVITIES/MAINTENANCE 09/25/73 73-'27A-59 ZMOLEK ATMOSPERIC HEAT ABSCRPTION C9/25/73 73-;27A-tC CRITES VOLCANIC STUDY 09/25/73 73-027A-61 HOPFIELD LIBRATICN CLCUDS 09/25/73 73-%27A-62 BUCHELER UBJECTS wITHIN MERCURY'S OROIT 09/25/73 73-027A-63 HAMILTON ULTRAVIOLET FROM QUASARS 09/25/73 73- 27A-64 REIHS X-RAY STELLAR CLASSES 09/25/73 73-327A-65 LEVENTHAL X RAYS FROM JUPITER 09/25/73 73-027A-66 SHANNCN uLTRAVIOLET FROM PULSARS 09/25/73 77-27A-67 STAEHLE BACTERIA AND SPORES 09/25/73 73-127A-68 MEISTER IN VITRC IMMUNOLOGY 09/25/73 73-227A-t- JACKSCN MOTOR SENSCRY PERFORMANCE 09/25/73 73-C27A-7C MILES WEt FORMATION 09/25/73 73-027A-71 WORGEKEMPER PLANT GROWTH AND PLANT PHOTUTROPISM 09/25/73 73-n27A-72 PELTZ CYTOPLASMIC STREAMING 09/25/73 73-C?27A-73 JCHNSTON CAPILLARY STUDY 09/25/73 73-0271-74 CONVERSE MASS MEASUREMENT 09/25/73 73-'27A-75 OLIST NEUTRON ANALYSIS 09/25/73 73-027A-76 DUNLAP LIGUID MOTION IN ZERO GRAVITY 09/25/73

1136 SECTION 3.3 - SPACECRAFT AND EXPERIMENTS WHICH BECANE INOPERABLE

The following table identifies spacecraft and/or experiments that became inoperable during the time interval between April 1, 1973, and March 31, 1974. The table is ordered alphabetically by spacecraft common name. For each spacecraft listed, the following information appears: the spacecraft common name, the NSSDC ID code, the spacecraft funding country/countries, the launch date, the date the spacecraft became inoperable, the orbit type, and the spacecraft orbit parameters (epoch date, apoapsis, periapsis, inclination, and period). The distance and time parameters are shown in km altitude and minutes except for heliocentric-type orbits, where they are shown in AU radial and days.

Experiments that have become inoperable are listed immediately below their associated spacecraft entry. The experiment NSSDC ID code, the experimenter's last name, the NSSDC experiment name, and the date the experiment became inoperable are given for each experiment. To indicate that a spacecraft was not placed in an inoperable mode, even though some of its experiments were in such a mode, the column indicating spacecraft inoperable date will appear blank.

When a prelaunch NSSDC ID code appears without a postlaunch NSSDC ID code, the particular spacecraft failed to orbit and was, therefore, not assigned an international designation.

1137 SPACECRAFT AND EXPERIMENTS WHICH BECAME INOPERABLE

* LAUNCH DATE S/C EPOCH ORBIT TYPE APO- PERI- INCLI- *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY DATE PLACED DATE APSIS APSIS NATION PERIOD *INOP

DATE EXP * * EXPERIMENTER EXPERIMENT NAME PLACED * , INOP 4

AE-C 73-121A UNITED STATES 12/16/73 / / 12/17/73 GEOCENTRIC 4303.0 158.0 68.1 132.5 73-ilA- & PELZ CLCSED SOURCE NEUTRAL MASS SPECTROMETER 02/17/74

AZROS 72-13nA FED. REP. OF GERMANY 12/16/72 08/22/73 12/16/72 GEOCENTRIC 864.7 218.0 96.9 95.5 72-ICCA-I KRANKCwSK DENSITY AND COMPOSITICN OF UPPER 08/22/73 ATMOSPHERE (2-44 AMU) 72-11CA-.2 SPENNEk ENERGY OISTRIBUTION OF IONS AND 08/22/73 ELECTRONS 7?-1('A-r3 NESKE ELECTRCN CCNCENTRATION IN THE IONOSPHERE 08/22/73 72-1CA-f4 SCHAIDTKE FLUX AND SPECTRAL DISTRIBUTION OF SOLAR 08/22/73 EUV RAD AND THEIR TEWP AND SPATIAL VAR 72-1ClA-C5 SPENCER NEUTRAL GAS TEMPERATURE IN THE 08/22/73 THERMCSPHERE 72-10.A-06 ROEMER ATMOSPHERIC DRAG ANALYSIS 08/22/73

APOLLO 15 LM/ALSEP 71-362C UNITEC STATES @7/26/71 / / LUNAR LANDER 71-f^hC-i3 DYAL LUNAR SURFACE MAGNETONETER 12/09/73

119.8 APOLLO 15 SUBSATELLITE 71-3630 UNITED STATES 08/C4/71 08/23/73 0 /04/71 SELENOCEN 141.3 102.0 28.7 71-0630-03 SJOGREN S-SAND TRANSPCNDER 08/23/73

APULLO 17 LM/ALSEP 72-'06C UNITEC STATES 12/07/72 / / LUNAR LANDER 72-296C-26 HOFFMAN ATMOSPHERIC COMPOSITICN 10/17/73

DS-A D-A FRANCE 04/27/73 04/27/73 FAILED TO ORBIT UNITED STATES

FAILED TO ORBIT 05-0 05-B FRANCE 04/27/73 04/27/73 UNITED STATES

IMP-L 67-O7CA UNITED STATES C7/19/67 06/24/73 07/22/67 SELENOCEN 9388.3 2568.0 169.0 691.8 67-37 A-01 VAN ALLEN ELECTRCN AND PROTON DETECTORS 06/24/73 07-C7CA-02 ANDERSON ENERGETIC PARTICLE 06/24/73 57-37CA- 3 SONETT AMES MAGNETIC FIELDS 06/24/73 67-07CA-C4 NESS GSFC MAGNETOMETER 06/24/73 67-27CA-05 ALEXANDER MICROMETEORITE FLUX 06/24/73 (7-07CA-7 SERBU LCW-ENERGY INTEGRAL SPECTRUM 06/24/73 MEASUREMENT EXPERIMENT 67-07CA-C8 PETERSON BISTATIC RADAR OBSERVATIONS OF THE LUNAR 06/24/73 SURFACE 67-]7A-29 KAULA SELENODETIC STUDIES 06/24/73 67-'7CA-IC SLIFER, JR. SOLAR CELL DAMAGE 06/24/73

IMP-H 72-273A UNITED STATES 09/23/72 / / 08/23/73 GEOCENTRIC 233231.0 202306.0 8.6 17602.0

pCDAGE BLA NOT FJlD 113 1139 SFPACEC$AFT ANhDKPEf-[IMENTs WHICH UECAME INOPP-RAJL

LAUNCH DATE S/C EPOCH ORBIT TYPt APO- PERI- INCLI- NATION PERIOD *SP'ACrLAFT rNA-I N-,-OL. [D FUNDING COUNTRY DATE PLACED DATE APSIS APSIS * INOP

4 DATE EXP * 4 _xEDP INENTRR EXPERINENT NAME PLACED * INOP *

72.-"7A-31 NES MAGNETIC FIELDS EXPERIMENT 04/10/73

ITO'-L [TS-F UNITED ETATCS 07/16/73 C7/16/7i FAILED TO ORBIT

25175.8 281.3 3.5 438.1 S-CUdED A 1I-'-fA UNITID STATLS 11/15/71 / / CS/,6/73 GEOCCNTRIC 71-)'9\j4-'4 CAHILL. JR, FLUXGATE MAGNETCMETCIS 04/01/73 71--gtA-' MAYNAGF, tDC ELECTRIC FIELD MEASUE'AENT 05/01/73

445.5 1.9 95.4 SAS-b 7r-14. UN1TE ST ThS 11/15/72 26/08/73 11/16/72 GEOCENTRIC 630.7 72-F,.A-i1 FICHTL GAWHA FAY TLLESCCPF 06/08/73

1 140 SECTION 4 - RECENT NSSDC DATA ACQUISITIONS

The following table identifies data acquired by NSSDC since July 1973 and not included in the last NSSDC supplement to the Data Catalog of Satellite Experiments. These data sets will be described in greater detail in future editions of the data catalog. During this interim, further information concerning these data sets or other NSSDC services may be obtained by directly contacting NSSDC.

This table is ordered alphabetically by spacecraft common name. In addition the table has a secondary ordering by NSSDC ID code. For each spacecraft listed, its common name, NSSDC ID code, funding country/ countries, launch date, and orbit type are given. For each experiment listed, the NSSDC ID code, the experimenter's last name, and the NSSDC experiment name are given. Listed for each data set are the NSSDC ID code,' the NSSDC data set name, the inclusive time period covered by the data set (MMDDYY), the time period verification code (VER), the data set availability code (AV), the data set form code (FM), and the data set quantity (QNTY).

The verification (VER) code is defined as follows:

V = time period verified by NSSDC.

E = time period provided by-the experimenter and not yet verified by NSSDC.

The availability (AV) code is defined as follows:

A = the data are at NSSDC, and NSSDC can supply a comprehensive set of documented data for routine requests.

B = the data are available in published reports.

C = the data are held at another center, although NSSDC has some information concerning the data set.

D = the data are at NSSDC and are being processed; i.e., work is continuing on a data set for which the documentation orprocessing is not complete.

E = the data are at NSSDC, and processing is deferred; i.e., this is a data set for which the documentation is not complete and on which no additional work will be performed unless specifically requested.

1141 F = the data are available from the experimenter; i.e., this is a data set that NSSDC does not plan to acquire, and the experimenter is willing to make it available to other scientists, usually in limited amounts.

M = the data are at another data center, but NSSDC will distribute limited portions of the data set in response to requests; i.e., the data sets are too large to be stored at NSSDC.

The data set form code (FM) is a two-letter code. The first code letter describes the basic form of the data set, and the second code letter describes the dimensions. The first code letter may be any of the following:

First Character Basic Type Units

A Aperture cards Cards B Books or bound volumes Each C Punched cards Each D Digital magnetic tapes Reels F Microfiche (black and white) Sheets G Microfiche (color) Sheets H Hardcopy Pages M Microfilm Reels 0 Computer graphic output Rolls P Computer printout Pages Q Black and white slides Each R Color slides Each S Strip or brush charts Rolls U Black and white positive film Each transparencies V Color positive film transparencies Each W Black and white prints Each X Color prints Each Y Black and white negatives Each Z. Color negatives Each

1142 The second code letter may be any of the following:

Second Character Additional Description

D 1/2 in. x 2400 ft E 2-1/4 x 2-1/4 in. F 3-1/4 x 4 in. G 4 x 5 in. H 5 x 7 in. I 8 x 10 in. J 11 x 14 in. K 16 x 20 in. L 20 x 24 in. M 70 mm N 9-1/2 in. 0 35 mm P 16 mm Q 3-1/4 x 7-5/8 in. R 4 x 6 in. S 5 x 8 in. T Various sizes U Bulk packaged material V 5 x 5 in. W 5 x 47-1/2 in. X 9-1/2 x 80 in.

1143 RECENT DATA ACQUISITIONS SINCE JULY 1973

LAUNCH DATE ORBIT TYPE *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY

* * TIME PERIOD VER AV FM ONTY S* EXPERIMENTER EXPERIMENT/DATA SET NAME

09/29/62 GEOCENTRIC ALOUETTE I 62-04SA CANADA UNITED STATES 62-049A-01 WHITTEKER SWEEP FREQUENCY SOUNDER DUCTED ECHOES 120162 123168 V A OD 1 62-049A-01Q INDEX OF IONOGRAMS SHOWING

11/29/65 GEOCENTRIC ALOUETTE 2 65-098A CANADA UNITED STATES 65-098A-01 WHITTEKER SWEEP FREQUENCY SOUNDER 112965 103071 V A DD 1 65-098A-OIN INDEX OF IGNOGRAMS SHOWING DUCTEC ECHOES

07/16/69 LUNAR LANDER APOLLO 11 LM/EASEP 6S-059C UNITED STATES 69-059C-01 SHOEMAKER LUNAR FIELD GEOLOGY SORTED BY 072069 072069 V D MP 1 69-059C-01G LUNAR SAMPLE DATA EASE LISTING SAMPLE NUMBER ON 16-MM MICROFILM

11/14/69 SELENOCENTRIC APOLLO 12 CSM 69-099A UNITED STATES 69-099A-12 SJOGREN S-BAND TRANSPONDER DATA. DERIVED FROM 111969 111969 V D MP 1 6S-099A-12A ANALYZED ACCELERATION RADIO TRACKING. Oh MICROFILM

11/14/69 LUNAR LANDER APOLLO 12 LM/ALSEP 69-099C UNITED STATES 69-099C-01 SHOEMAKER LUNAR FIELD GEOLOGY SORTED BY 111969 112069 V 0 MP 1 69-099C-01G LUNAR SAMPLE DATA EASE LISTING SAMPLE NUMBER ON 16-MM MICROFILM 69-099C-03 LATHAM PASSIVE SEISMIC D DD 69-099C-03A SEISMCGRAMS ON MAGNETIC TAPE 112069 102672 V 128 111969 050973 V D MO 2 69-099C-03B COMPRESSED TIME SCALE PLOTS OF LUNAR SEISMIC DATA ON 35-MM MICROFILM OF SELECTED 112069 073171 V D MO 1 69-099C-03C COMPRESSED TIME SCALE PLOTS LUNAR SEISMIC EVENTS ON 35-MM MICROFILM OF SELECTED 112669 08872 V D MO 3 69-099C-03D EXPANDED TIME SCALE PLAYOUTS LUNAR SEISMIC EVENTS ON 35-MM MICROFILM DATA ON 112069 3E0370 V D DO 2 69-099C-03F ARTIFICIAL LUNAR INPACT SEISMIC MAGNETIC TAPE ON 1120E9 042173 V 0 DO 1 69-099C-03G SEISMIC EVENT LOG AS CARD IMAGES MAGNETIC TAPE 69-099C-04 SONETT LUNAR SURFACE MAGNETOMETER VECTORS ON TAPE 111969 040370 V 0 DD 35 69-099C-04B 0.3-SEC MAGNETIC 69-099C-09 SJOGREN S-BAND TRANSPONDER DERIVED FROM 111969 111969 V D MP I 69-099C-09A ANALYZED ACCELERATION DATA, RADIO TRACKING. ON MICROFILM

01/31/71 SELENOCENTRIC APOLLO 14 CSM 71-008A UNITED STATES

PEBLON4DIGE NOT FI E 1145 RECENT DATA ACQUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY DATE ORBIT TYPE

S* EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM ONTY

71-OO8A-01 UNKNCWN ORBITAL AND SURFACE PHOTOGRAPHY 71-OO8A-OIM LUNSORT PHOTOGRAPHIC SUPPORT DATA BY LAC 020471 020771 V D DD 2 AREA ON MAGNETIC IAPE 71-008A-03 SJOGREN S-BAND TRANSPONDER 71-OOeA-03B ANALYZED ACCELERATION DATA, DERIVED FROM 020471 020571 V D MP I RADIO TRACKING, ON MICROFILM 71-00C8A-04 HOWARD DCWN-LINK BISTATIC RADAR OBSERVATIONS 71-008A-04A REDUCED SHORT TIME AVERAGES ON 13-CM 020671 020671 V O DD 1 BISTATIC RADAR LUNAR OBSERVATIONS ON TAPE 71-OOBA-04B REDUCED SHORT TIME AVERAGES ON 116-CM 020671 020671 V D DD 1 BISTATIC RADAR LUNAR OBSERVATIONS ON TAPE 71-008A-04C ANALYZED 13-CM AND 116-CM BIASTIC RADAR 020671 023671 V D DD I LUNAR OBSERVATIONS ON MAGNETIC TAPE

APOLLO 14 LM/ALSEP 71-008C UNITED STATES 01/31/71 LUNAR LANDER 71-OCeC-01 SWANN LUNAR FIELD GEOLOGY 71-008C-01G LUNAR SAMPLE DATA BASE LISTING SORTED BY 020371 020471 V D MP 1 SAMPLE NUMBER ON 16-MM MICROFILM 71-00OC-04 LATHAM PASSIVE SEISMIC 71-OOeC-04B MAGNETIC TAPES OF LUNAR SEISMIC EVENTS 020671 1C2672 V D DD 102 71-00C-04C COMPRESSED TIME SCALE PLOTS OF LUNAR 020571 051173 V D MO 2 SEISMIC DATA ON 35-MM MICROFILM 71-008C-04D EXPANDED TIME SCALE PLAYOUTS OF LUNAR 020771 080872 V D MO 2 SEISMIC DATA ON 35-MM MICROFILM 71-00C-04E COMPRESSED TIME SCALE PLOTS OF LUNAR 020671 073171 V D MO 1 SEISMIC EVENTS ON 35-MM MICROFILM 71-008C-04F ARTIFICIAL LUNAR IMPACT SEISMIC DATA ON 020771 121671 V D DO I MAGNETIC TAPE 71-00eC-0O O'BRIEN CHARGED PARTICLE LLNAR ENVIRONMENT 71-OO8C-08B EXPERIMENT POSITION AND ORIENTATION 010171 123173 V D DD 1 INFORMATION VS TINE ON TAPE 71-OOeC-11 SJOGREN S-BAND TRANSPONDER 71-008C-11A ANALYZED ACCELERATION DATA, DERIVED FROM 020771 020771 V D MP 1 RADIO TRACKING. ON MICROFILM

APOLLO 15 CSM 71-063A UNITED STATES 07/26/71 SELENOCENTRIC 71-063A-01 DOYLE HANDHELD PHOTOGRAP-Y 71-063A-01J CAL TECH MICROFICHE OF HASSELBLAD 70-MM 072671 080771 V D FR 42 PHOTCGRAPHY ON 4- X 6-IN. B/W FILM CARDS 71-063A-OIP COMPLETE NIKON CAMERA DIMLIGHT 072771 080771 V A UO 1 PHOTOGRAPHY ON 35-MM FILM 71-063A-OIR HASSELBLAD CAMERA PHOTOGRAPHY INDEX ON 072671 080771 V D FR 6 MICROFICHE 71-063A-02 DOYLE PANCRAMIC PHOTOGRAPHY

1146 RECENT DATA ACQUISITIONS SINCE JULY 1973

LAUNCH DATE ORBIT TYPE *SPACECRAFT NAME NSSOC ID FUNDING COUNTRY

* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * . * * * * * * * * * * * * * * * * * * * * * SET NAME TIME PERIOD VER AV FM ONTY -* * EXPERIMENTER EXPERIMENT/DATA

INDEX 073171 080371 V A FR 4 71-063A-02H NSSDC PANORAMIC CAMERA PHOTOGRAPHY ON MICROFICHE 71-063A-03 DOYLE METRIC PHCTOGRAPHY INDEX ON 073171 080371 V A FR 4 71-063A-031 NSSDC METRIC CAMERA PHOTOGRAPHY B/% MICROFICHE 71-063A-11 SJOGREN S-BAND TRANSPONDER (CSM/LM) DERIVED FROM 033071 033171 V D MP 1 71-063A-118 ANALYZED ACCELERATION DATA. RADIO TRACKING. ON MICROFILM 71-063A-14 HOWARD BISTATIC RADAR OF 13-CM 080171 080171 V D DO 2 71-063A-14A REDUCED SHORT TIME AVERAGES BISTATIC RADAR LUNAR OBSERVATIONS ON TAPE 116-CM 080171 080171 V D DO 1 71-063A-148 REDUCED SHORT TIME AVERAGES OF BISTATIC RADAR LUNAR OBSERVATIONS ON TAPE RADAR 080171 080171 V D DO 1 71-063A-14C ANALYZED 13-CM AND 116-CM BIASTIC LUNAR OBSERVATIONS ON MAGNETIC TAPE

07/26/71 LUNAR LANDER APOLLO 15 LM/ALSEP 71-063C. UNITED STATES 71-063C-01 LATHAM PASSIVE SEISMIC 080271 102672 V D DO 75 71-063C-01B SEISMOGRAMS ON MAGNETIC TAPE 080471 080872 V 0 MO 2 71-063C-01C EXPANDED TIME SCALE PLAYOUTS OF LUNAR SEISMIC DATA ON 35-MM MICROFILM LUNAR 080471 051673 V D MO 2 71-063C-01D COMPRESSED TIME SCALE PLOTS OF SEISMIC DATA ON 35-MM MICROFILM 71-063C-10 SWANN LUNAR FIELD GEOLOGY BY 073171 080271 V D MP I 71-063C-10F LUNAR SAMPLE DATA EASE LISTING SORTED SAMPLE NUMBER ON 16-MM MICROFILM

SELENOCENTRIC APOLLO 15 SUBSATELLITE 71-0630 UNITED STATES 08/04/71 71-063D-01 ANDERSON LUNAR PARTICLE SHADOWS AND BOUNDARY LAYER COUNT 080471 02037? V D DD I 71-063D-01A 10-MIN AND 2-HR AVERAGED PARTICLE RATES ON MAGNETIC TAPE

SELENOCENTRIC APOLLO 16 CSM 72-031A UNITED STATES 04/16/72 72-031A-01 DOYLE HANDHELD PHOTOGRAPHY 041672 042772 V D MP 2 72-031A-011 NSSOC CATALOG OF HASSELBLAD PHOTOS ON MICROFILM ON 041672 042772 V A FR 60 72-031A-OIJ NSSOC HASSELBLAD PICTORIAL CATALOG MICROFICHE ON 041672 042772 V A MP 1 72-031A-01K INDEX TO 70-MM HASSELBLAD PHOTOGRAPHY 16-MM MICROFILM 041672 042772 V A MP 1 72-031A-OIL INDEX TO 16-MM MAURER PHOTOGRAPHY ON 16-MM MICROFILM 72-031A-02 DOYLE PANCRAMIC PHCTOGRAPHY

1147 RECENT DATA ACQUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY DATE ORBIT TYPE

S* EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM ONTY

72-031A-02D CCMPLETE PANORAMIC CAMERA PHOTOGRAPHY 042172 042672 V A MO 1 CATALOG ON 35-MM E/W MICROFILM 72-031A-02E RECTIFIED PANORAMIC CAMERA PHCTOGRAPHY ON 042172 042672 V A UX 16 9- BY 80-IN. B/W FOSITIVE FILM 72-031A-03 DOYLE METRIC PHCTOGRAPHY 72-031A-03E NSSDC CATALOG OF METRIC PHOTOGRAPHY ON 042172 042672 V A MP 2 MICRCFILM 72-031A-03F COMPLETE MAPPING CAMERA PHOTOGRAPHY 042172 042672 V A FR 57 CATALOG CN B/W POSITIVE MICROFICHE 72-031A-04 DOYLE MAPPING CAMERA ASPECT STELLAR PHOTCGRAPHY 72-031A-04A MAPPING CAMERA STELLAR PHOTOGRAPHY ON 042172 042672 V 0 UM 1 70-MM MASTER POSITIVE FILM 72-031A-12 HOWARD BISTATIC RADAR 72-031A-12A REDUCED SHORT TIME AVERAGES OF 13-CM 042372 042372 V D DD 2 BISTATIC RADAR LUNAR OBSERVATIONS ON TAPE 72-031A-128 REDUCED SHORT TIME AVERAGES OF 116-CM 042372 042372 V D DD 1 BISTATIC RADAR LUNAR OBSERVATIONS ON TAPE 72-031A-12C ANALYZED 13-CM AND 116-CM BIASTIC RADAR 042372 042372 V D DD 1 LUNAR CBSERVATIONS ON MAGNETIC TAPE 72-031A-15 GARY SKYLAe-APCLLO CONTAMINATION PHOTOGRAPHY 72-031A-15A DIGITIZED CONTAMINATION PHOTOGRAPHY ON 041672 042772 E A DD 1 MAGNETIC TAPE

APOLLO 16 LM/ALSEP 72-031C UNITED STATES 04/16/72 LUNAR LANDER 72-031C-01 LATHAM PASSIVE SEISMIC 72-031C-018 SEISMOGRAMS ON MAGNETIC TAPE 042172 1C2672 V D DD 35 72-031C-01C EXPANDED TIME SCALE PLAYOUTS OF LUNAR 050272 080872 V 0 MO 2 SEISMIC DATA ON 35-MM MICROFILM 72-031C-01D COMPRESSED TIME SCALE PLOTS OF LUNAR 090271 050773 V D MO 2 SEISMIC DATA ON 35-MM MICROFILM 72-031C-01E ARTIFICIAL LUNAR IMPACT SEISMIC DATA ON 121072 121572 V 0 DO 1 MAGNETIC TAPE 72-031C-05 MUEHLBERGER LUNAR FIELD GEOLOGY 72-031C-05B LUNAR SAMPLE DATA EASE LISTING SORTED BY 342172 C42472 V D MP 1 SAMPLE NUMBER ON 16-MM MICROFILM

APOLLO 16 SUSSATELLITE 72-0310 UNITED STATES 04/24/72 SELENOCENTRIC 72-0310-01 ANDERSON LUNAR PARTICLE SHACOWS AND BOUNDARY LAYER 72-031D-01A 10-MIN AND 2-HR AVERAGED PARTICLE COUNT 042572 052972 V D DO 1 RATES ON MAGNETIC TAPE

APOLLO 17 CSM 72-096A UNITED STATES 12/07/72 SELENOCENTRIC

1148 RECENT DATA ACQUISITIONS SINCE JULY 1973

*LAUNCH *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY DATE ORBIT TYPE

* EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM ONTY

72-096A-05 DOYLE HANDHELD PHOTOGRAP-Y 72-096A-058 COMPLETE HASSELBLAD PHOTOGRAPHY ON 8/W 120772 121972 V D UM 2 POSITIVE FILM 72-096A-05C COMPLETE COLOR HASSELBLAD PHOTCGRAPHY ON 120772 121972 V D VM 2 70-MM FILM 72-096A-05D NIKCN PHOTCGRAPHY 120772 121972 V D UO 1 72-096A-05E CALTECH CATALOG OF HASSELBLAD PHOTOGRAPHY 120772 121972 V D FR 52 CN MICROFICHE 72-09tA-05G LUNAR SURFACE TV KINESCOPE PHOTOGRAPHY 121272 121872 V D UP39095 ON 16-MM B/W POSITIVE FILM 72-096A-06 DOYLE PANCRAMIC PHOTOGRAPHY 72-096A-06A 5- BY 48-IN. B/W SECOND GENERATION 121072 121672 V D UW 23 MASTER POSITIVE PANORAMA PHOTOS 72-096A-068 PANORAMIC CAMERA PI-OTOGRAPHY SUPPORT DATA 121072 121672 V D MP I ON 16-MM MICROFILM 72-096A-06D NSSDC CATALOG OF PANORAMIC CAMERA PHOTOS 121072 121672 V D MO 1 ON 35-MM MICROFILM 72-096A-07 DOYLE METRIC PHOTOGRAPHY 72-096A-07C MAPPING CAMERA PHOTOGRAPHY SUPPORT DATA 121072 121672 V D MP 1 ON 16-WM MICROFILM 72-096A-07D CAL TECH CATALOG OF METRIC PHOTOGRAPHY 121172 121672 V D FR 76 ON MICROFICHE

APOLLO 17 LM/ALSEP 72-096C UNITED STATES 12/07/72 LUNAR LANDER 72-096C-02 SWANN LUNAR FIELD GEOLOGY 72-096C-028 LUNAR SAMPLE DATA EASE LISTING SORTED BY 121172 121372 V D MP 1 SAMPLE NUMBER ON 16-MM MICROFILM

ARIEL 3 67-042A UNITED STATES 05/05/67 GEOCENTRIC UNITED KINGDOM 67-042A-01 SAYERS LANGNUIR PROBE 67-042A-01C ELECTRON DENSITY AND TEMPERATURE PLOTS ON 050567 041568 V D MO 3 MICRCFILM 67-042A-01D ELECTRON DENSITY AND TEMPERATURE LISTINGS 050667 123167 V D MO 3 ON MICROFILM

ESSA 3 66-087A UNITED STATES 10/C2/66 GEOCENTRIC 66-087A-01 NESS STAFF ADVANCED VIDICON CAMERA SYSTEM (AVCS) 66-087A-OIA GLOBAL DAILY NEPHANALYSIS OF SATELLITE 100466 123166 V B BI 1 CLCUD CBSERVATIONS

ESSA 5 67-036A UNITED STATES 04/20/67 GEOCENTRIC 67-036A-01 NESS STAFF ADVANCED VIDICON CAMERA SYSTEM (AVCS) 67-036A-01A CATALOG OF METEOROLOGICAL SATELLITE DATA- 060167 090368 V" B BI 4

1149 RECENT DATA ACQUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSDC ID FUNDING COUNTRY DATE OROIT TYPE

* EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM ONTY

ESSA 5 TELEVISION CLOUD PHOTOGRAPHY

ESSA 7 68-069A UNITED STATES 08/16/68 GEOCENTRIC 68-C69A-01 NESS STAFF ACVANCED VIDICON CAMERA SYSTEM (AVCS) 68-069A-01A CATALOG OF METEOROLOGICAL SATELLITE DATA- 090368 033169 V B BI 3 ESSA 7 TELEVISION CLOUD PHOTOGRAPHY

ESSA 9 69-016A UNITED STATES 02/26/69 GEOCENTRIC 69-016A-01 NESS STAFF ADVANCED VIDICON CAMERA SYSTEM (AVCS) 69-016A-OIA CATALOG OF METEOROLOGICAL SATELLITE DATA- 040169 06167- V B 1 7 ESSA 9 TELEVISION CLOUD PHOTOGRAPHY

GRS-A 69-097A FED. REP. OF GERMANY 11/08/69 GEOCENTRIC UNITED STATES 69-097A-02 HOVESTADT PROTCN-ALPHA TELESCOPE 69-097A-02A PROTON, ALPHA PARTICLE AND ELECTRCN COUNT 110869 06187r E D DD 15 RATES ON MAGNETIC TAPE 69-097A-03 MORITZ PROTCN TELESCOPE 69-097A-03D PLOTS OF PROTON ANC ALPHA PARTICLE COUNT 110869 06287 V D MP 1 RATES AND FLUXES CN MICROFILM 69-097A-04 HOVESTADT PROTCN-ELECTRON DETECTOR 69-097A-04A PROTON ANC ELECTRON COUNT RATES ON 110869 C61870 E D OD 14 MAGNETIC TAPE

IMP-F 67-051A UNITED STATES 05/24/67 GEOCENTRIC 67-051A-11 NESS TRIAXIAL FLUXGATE MAGNETOMETER 67-051A-11D 2.5-SEC MULTICOCRDINATE MAGNETIC VECTORS 052467 021C69 V D DD 136 ON TAPE

IMP-G 6S-053A UNITED STATES 06/21/69 GEOCENTRIC 69-053A-OOG GSFC TRAJECTORY PLCTS. SOLAR ECLIPTIC 062169 122372 V B RI 1 PROJECTIONS 69-053A-02 ANDERSCN ICN CHAMBER 69-053A-02B ELECTRON AND PROTON COUNT RATES ON 062169 083172 V D MO 5 MICRCFILM

IMP-H 72-073A UNITED STATES 09/23/72 GEOCENTRIC 72-073A-00D GSFC TRAJECTORY PLETS. SOLAR ECLIPTIC 092372 04C673 V 8 BI 1 PRCJECTIONS

IMP-I 71-019A UNITED STATES 03/13/71 GEOCENTRIC 71-019A-09 SIMPSON NUCLEAR COMPOSITION OF COSMIC AND SULAR PARTICLE RADIATIONS 71-019A-OSA PROTON ANC HIGHER 2 COUNT RATES ON 031371 01C672 V 0 DD 18 MAGNETIC TAPE

1150 RECENT DATA ACOUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSCC ID FUNDING CCUNTRY DATE ORBIT TYPE

4 * * EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM ONTY

71-019A-098 5-MIN AVERAGED PROTON AND HIGHER Z 031371 040172 V 0 DD 1 COUNT RATES ON MAGNETIC TAPE

ISIS 1 69-009A CANADA 01/30/69 GEOCENTRIC UNITED STATES 69-009A-01 WHITTEKER SWEEP FREQUENCY SOUNDER 69-009A-01E INDEX OF IONOGRAMS SHOWING DUCTEC ECHOES 020169 122771 V A DO 1 69-009A-08 SAGALYN SPHERICAL ELECTROSTATIC ANALYZER 69-009A-08A ION DENSITY ON 35-WM FILM 013169 022569 V D MO 1 69-009A-08a ION TEMPERATURE ANC DENSITY ON MAGNETIC 020069 110069 V D DO 4 TAPE

ISIS 2 71-024A CANADA 04/01/71 GEOCENTRIC UNITED STATES 71-024A-01 WHITTEKER SWEEP FREQUENCY SCUNDER 71-024A-01E INDEX OF IONOGRAMS SHOWING DUCTED ECHOES 040971 062272 V A DD 1

MARINER 4 64-077A UNITED STATES 11/28/64 HELIOCENTRIC 64-077A-02 SMITH HELIUM MAGNETOMETER 64-077A-02C 2.8-MIN AVG MAGNETIC'FIELD MEASUREMENTS 112964 100165 V 0 MO 1 PLOTTED 1 DAY PER 35-MM MICROFILM FRAME 64-077A-02D 4.2-SEC MAGNETIC FIELD MEASUREMENTS 112964 010365 V 0 MO 1 PLCTTED 1 HR PER 35-MM MICROFILM FRAME 64-077A-02E 16.8-SEC MAGNETIC FIELD MEASUREMENTS 010365 100165 V 0 MO 1 PLOTTED 3 HR PER 35-MM MICROFILM FRAME

MARINER 9 71-051A UNITED STATES 05/30/71 MARSCENTRIC 71-051A-03 HANEL INFRARED INTERFEROMETER SPECTROMETER (IRIS) 71-051A-03A INFRARED INTERFEROMETER SPECTROMETER DATA 111471 1C1672 V D DD 5 TAPES 71-051A-04 MASURSKY TELEVISION PHOTOGRAPHY 71-051A-04H TV PHCTOGRAPHIC SUPPORTING DATA ON 16-MM 111471 102772 V D MP 1 MICRCFILM 71-051A-041 TV PHOTOGRAPHY INDEX DATA ON 16-MM O/W 111471 102772 V D MP 2 NEGATIVE FILM 71-051A-04J IPL MICROFICHE CATALOG OF SELECTED 111071 080672 V D FR 279 PHOTOGRAPHY 71-051A-04L CATALCG OF MARINER 9 MTVS PHOTOGRAPHY 111071 080672 V 0 MP 20 ON 16-MM MICROFILM 71-051A-040 LIME PHOTOGRAPHY INDEX ON B/W MICROFICHE 111071 102872 V D FR 16 71-051A-04P LIMB PHOTOGRAPHY CATALOG ON A/W 111071 102872 V D FR 166 MICROFICHE 467 71-051A-04Q SELECTED MTVS AND IPL PHOTOGRAPHY ON 111071 102872 V D FR MICROFICHE FROM CAL TECH

1151 RECENT DATA ACQUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSOC ID FUNDING COUNTRY DATE ORBIT TYPE

S* EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM ONTY

NIMBUS 2 66-040A UNITED STATES 05/15/66 GEOCENTRIC 66-040A-01 SCHULMAN ADVANCED VIDICON CAMERA SYSTEM (AVCS) 66-040A-018 AVCS hORLD MONTAGE CATALOG 051566 111566 V B BT 1

NIMBUS 4 70-025A UNITEC STATES 04/08/70 GEOCENTRIC 70-025A-03 HANEL INFRARED INTERFEROPETER SPECTROMETER (IRIS) 70-025A-03A INFRARED INTERFEROMETER SPECTROMETeR 040970 013071 E M DO 238 (IRIS) RADIANCE TAPES

NIMBUS 5 72-097A UNITED STATES 12/11/72 GEOCENTRIC 72-097A-04 WILHEIT, JR. ELECTRICALLY SCANNING MICROWAVE RADICMETER (ESMR) 72-097A-04A ELECTRICALLY SCANNING MICROWAVE 121572 C61273 E M DO 198 RADIOMETER (ESMR) DATA TAPES 72-097A-04B SELECTED ESMR COLOR IMAGES 121572 021073 V D ZI 44

NOAA 2 72-082A UNITED STATES 10/15/72 GEOCENTRIC 72-082A-02 NESS STAFF SCANNING RADIOMETEF (SR) 72-082A-02A CATALOG OF ENVIRONNENTAL SATELLITE 110172 063073 V B BJ 6 IMAGERY

OGO 1 64-054A UNITED STATES 09/05/64 GEOCENTRIC 64-054A-21 WINCKLER ELECTRON SPECTROMETER 64-054A-211 REDLCED L-INTERPOLATED COUNT RATES ON 091564 070767 V D DD 1 MAGNETIC TAPE

OGO 5 68-014A UNITED STATES 03/04/68 GEOCENTRIC 68-014A-04 ANDERSON ENERGETIC RADIATIONS FROM SOLAR FLARES 68-014A-04C PROTON AND ALPHA PARTICLE COUNT RATES ON 030868 111769 V D DD 2 MAGNETIC TAPE 68-014A-0S MEYER COSNIC PAY ELECTRONS 68-014A-098 PARTICLE ACCUMULATIONS AND PULSE HEIGHT 030568 071472 V D DO 109 ANALYSIS ON MAGNETIC TAPE 68-014A-16 SMITH TRIAXIAL SEARCH-COIL MAGNETOMETER 68-014A-16D FREQUENCY TIME SPECTROGRAMS FOR THE 030668 1027b8 V 0 MO 27 0-1000 HZ ANALOG SEARCH COIL PAGNETOMETER 68-014A-20 HADDOCK 50 KHZ TO 3.5 MHZ SOLAR RADIO ASTRONOMY IN EIGHT STEPS 68-014A-20A 8-CHANNEL FREQUENCY VS TIME PLOTS OF 030568 092471 V F MO 50 SOLAR RADIO EMISSIONS ON MICROFILM 68-014A-22 BLAMONT GEGCCRONAL LYMAN-ALPHA MEASUREMENT 68-014A-22A LYMAN ALPHA GEOCORCNAL DATA ON MAGNETIC 030568 123169 V 0 DD 32 TAPES

1152 RECENT DATA ACQUISITIONS SINCE JULY 1973

LAUNCH *SPACECRAFT NAME NSSOC ID FUNDING CGUNTRY DATE ORFIT TYPE

* * EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM GNTY

68-014A-24 CROOK PLASMA WAVE DETECTCR 68-014A-24E C-IC KHZ SPECTRA CF MAGNETOSPHERIC AND 031468 051269 V D MO 14 PLASMASPHERIC BOUNDARIES ON MICROFILM 68-014A-27 SIMPSON LCw-ENERGY HEAVY CCSMIC-RAY PARTICLES (HIGH-Z LOW-E EXPERIMENT) 68-314A-278 COUNT RATE PLCTS GF MICROFILM 030568 C71372 V D MO 1

OGO 6 69-051A UNITEC STATES 06/05/69 GEOCENTRIC 69-051A-20 STONE CCSMIC-RAY STUDY 69-051A-20B PARTICLE COUNT RATES AND EPHEMERIS PLOTS 060769 012770 V 0 MO 28 ON MICROFILM 69-051A-22 SMITH TRIAXIAL SEARCH COIL MAGNETOMETER 69-051A-22A 0.03- TO 1000-HZ SEARCH COIL 061069 101370 V D MP 5 MAGNETCMETER

OVI- 2 65-07eA UNITED STATES 10/05/65 GEOCENTRIC 65-078A-03 FORTNEY X-RAY CSI CRYSTAL COSIMETER 65-07EA-03A TABULATIONS OF ANALYZED DOSIMETER DATA ON 100565 12C165 V B HI 10 HARDCOPY

OVI-15 6E-059A UNITED STATES 07/11/68 GEOCENTRIC 68-059A-01 CHAMPICN TRIAXIAL ACCELEROMETER 68-059A-01A TRIAXIAL ACCELEROMETER ATMOSPHERIC 071468 092868 V B BI 1 DENSITY PLOTS

PIONEER 6 65-105A UNITED STATES 12/16/65 HELIOCENTRIC 65-105A-02 BRIDGE SOLAR WIND PLASMA FARADAY CUP 65-105A-02C SCLAR WIND DATA FRCM THE EXPERIMENTS ON 121665 051,71 V a BI 1 PICNEER 6 AND PICNEER 7. 1 HR AVG BOOK

PIONEER 7 66-075A UNITED STATES 08/17/66 HELIOCENTRIC 66-075A-02 BRIDGE SOLAR WIND PLASMA FARADAY. CUP 66-075A-02C SCLAR WIND DATA FRCM THE EXPERIMENTS ON 081866 121268 V 8 BI I PICNEER 6 AND PICNEER 7, 1 HR AVG BOOK

PIONEER 8 67-123A UNITED STATES 12/13/67 HELIOCENTRIC 67-123A-05 MCCRACKEN COSMIC-RAY ANISOTRCPY 67-123A-05A 7.5-MIN AND I-HR CCUNT RATES FOR ALL 121367 033169 V D DD 6 MODES ON MAGNETIC TAPE

PIONEER 9 68-I00A UNITED STATES 11/08/68 HELIOCENTRIC 68-I00A-05 MCCRACKEN COSMIC-RAY ANISOTRCPY 68-100A-05A 7.5-MIN AND 1-HR CCUNT RATES ON 110868 02570 V A MP 2 MICRCFILM

1153 RECENT DATA ACQUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSDC ID FUNDING CCUNTRY DATE ORBIT TYPE

** EXPERIMENTER EXPERIMENT/DATA SET NAME TIME PERIOD VER AV FM QNTY

RELAY I 62-068A UNITED STATES 12/13/62 GEOCENTRIC 62-068A-03 MCILWAIN PROTON-ELECTRON DETECTORS 62-068A-03A. FORTRAN PROTCN FLUX PROGRAM 010163 070163 V A CO 3000

TIROS 1 60-002B UNITED STATES 04/01/60 GEOCENTRIC 60-0028-01 BUTLER TELEVISION CAMERA SYSTEM 60-0028-01A INDEX OF METEORCLOGICAL SATELLITE DATA - 040160 061560 V B BI 1 TIROS I TELEVISION CLOUD PHOTOGRAPHY 60-0028-018 35-MM DAYTIME TV CLOUD PHCTOGRAPHY 040160 061560 E C MO 50

TIROS 2 60-01EA UNITED STATES 11/23/60 GEOCENTRIC 60-016A-03 BUTLER TELEVISION CAMERA SYSTEM 60-016A-03A INDEX OF METEOROLOGICAL SATELLITE DATA - 112360 092761 V 8 BI I TIROS 2 TELEVISION CLOUD PHOTOGRAPHY 60-C16A-03B 35-WM DAYTIME TV CLOUD PHOTOGRAPHY 112360 092761 E C MC 56

TIROS 3 61-017A UNITEC STATES 07/12/61 GEOCENTRIC 61-017A-04 NESS STAFF TELEVISION CAMERA SYSTEM 61-017A-04A INDEX OF METEOROLOGICAL SATELLITE DATA - 071261 012362 V B BI 1 TIROS 3 TELEVISION CLOUD PHOTOGRAPHY 61-C017A-04B 35-NM DAYTIME TV CLOUD PHOTOGRAPHY 071261 012362 E C MO 70

TIROS 4 62-002A UNITEC STATES 02/C8/62 GEOCENTRIC 62-002A-000 ATTITUDE SUMMARY TABLES 020862 061262 V 8 81 1 62-002A-04 NESS STAFF TELEVISION CAMERA SYSTEM 62-002A-04A GLOBAL DAILY NEPHAhALYSIS OF SATELLITE 020862 061862 V B BI I CLCOD CBSERVATIONS 62-002A-048 35-MM .DAYTIME TV CLOUD PHOTOGRAPHY 020862 061862 E C MO 72

TIROS 5 62-025A UNITED STATES 06/19/62 GEOCENTRIC 62-025A-01 NESS STAFF TELEVISION CAMERA SYSTEM 62-02SA-OIA GLOBAL DAILY NEPHANALYSIS OF SATELLITE 061962 051463 V B BI 1 CLCUD CBSERVATIONS 62-025A-018 35-MM DAYTIME TV CLOUD PHCTOGRAPHY 061962 051463 E C MO 113

TIROS 6 62-047A UNITED STATES 0S/18/62 GEOCENTRIC 62-047A-01 NESS STAFF TELEVISION CAMERA SYSTEM 62-047A-CIA GLOBAL DAILY NEPHANALYSIS OF SATELLITE 091862 102163 V B BI 1 CLOUD CBSERVATIONS 62-047A-018 35-MM DAYTIME TV CLOUD PHOTOGRAPHY 091862 051463 E C MO 125

TIROS 7 63-024A UNITED STATES 06/19/63 GEOCENTRIC 63-024A-04 NESS STAFF TELEVISION CAMERA SYSTEM 63-024A-04A GLOEAL DAILY NEPHANALYSIS OF SATELLITE 061963 123165 V B B1 4

1154 RECENT DATA ACQUISITIONS SINCE JULY 1973

SLAUNCH *SPACECRAFT NAME NSSOC ID FUNDING COUNTRY DATE ORBIT TYPE

***g agesC 4 ***** * * * ** *** * * * * *& * * * *4** * * * * * * * ** * * * * ** * * *

TIME PERIOD VER AV FM ONTY * * EXPERIMENTER EXPERIMENT/DATA SET NAME

CLCUD OBSERVATIONS C MO 213 63-024A-04B 35-MM DAYTIME TV CLOUD PHOTOGRAPHY 061963 022666 E

TIROS 8 63-054A UNITED STATES . 12/21/63 GEOCENTRIC 63-054A-01 NESS STAFF TELEVISION CAMERA SYSTEM 3 63-054A-01A GLOBAL DAILY NEPHANALYSIS OF SATELLITE 122163 083165 V B BI CLOUD OBSERVATIONS C 163 63-054A-018B 35-M DAYTIME TV CLOUD PHOTOGRAPHY 122163 021266 E MO

TIROS 9 65-004A UNITED STATES 01/22/65 GEOCENTRIC 65-004A-01 NESS STAFF TELEVISION CAMERA SYSTEM V B 8I 2 65-004A-01A GLOBAL DAILY NEPHANALYSIS OF SATELLITE 012365 072665 CLOUD CBSERVATIONS C MO 133 65-004A-01B 35-MM DAYTIME TV CLOUD PHOTOGRAPHY 012365 090866 E

TIROS 10 65-051A UNITED STATES 07/02/65 GEOCENTRIC 65-051A-01 NESS STAFF TELEVISION CAMERA SYSTEM 1 65-051A-1A GLOBAL DAILY NEPHANALYSIS OF SATELLITE 070465 03065 V 8 BI CLOUD CBSERVATIONS MO 56 65-051A-01B 35-MM DAYTIME TV CLOUD PHOTOGRAPHY 070265 042066 E C

1155